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MAESTRO Manual - Design Systems & Technologies

1. 1 18E 003 1 94E 003 2 70E 003 3 46E 003 4 21E 003 4 97E 003 73E 003 Figure 11 Align Stress to Global X SigX 9 2E02 SigY 6 66 Tau 613 96 top s2 midbody m1 fr 25 49 strake 16 Quad Sec 1 Thickness 0 5 in SigY 9 2000E 002 Tau 613 962 SigVM 1 4040E 003 Corner Stress VM1 1 6070E 003 VM2 1 7398E 003 VM3 1 2876E 003 VM4 1 1156E 003 1 18E 003 1 94E 003 2 70E 003 3 46E 003 4 21E 003 4 97E 003 5 73E 003 Figure 12 Align Stress to Global Z SigX 6 66 SigY 9 2E02 Tau 613 96 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 309 The directional stress option can be toggled on by selecting Results gt Stress gt Directional from the menu A check mark will appear next to this option when it is turned on The direction for each element can be displayed with a quill by selecting Results gt Stress gt Show Direction from the menu A check mark will appear next to this option when it is turned on The length of the quill can be adjusted in the View Options dialog Figure 13 demonstrates the 6 user defined stress directions on the directional stress mdl model The blue quills represent the new element local x direction after the adjusted alignment This model can be found in t
2. Properties The View Longitudinal gt Properties command under the Hull menu displays the hull girder properties for each section in table form in the Grid tab Within the grid the user can select individual sections to view or copy the results and paste them into another program such as Microsoft Excel 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 LM UVE RRP PPP EEAEBASEo Status Izz V in 4 lyy H in 4 3 in 4 Area in 2 AreaZ in 2 AreaY in 2 Neutral Axis Z in Neutral Axis Y in Shear Center Z in Shear Center Y in Y DK2NA in Y BL2N 12 6 OK 1 51733e 006 622631 1 78333e 006 7 89501e 009 255 603 155 71 123 733 2 07077e 016 127 523 3 40781e 014 221 011 160 477 11 E5 7 96 OK 1 51733e 006 622631 1 78333e 006 7 89501e 009 255 603 155 71 123 733 6 21232e 016 127 523 3 23479e 014 221 011 160 477 P 14 7 120 OK 1 71415e 006 991160 2 51948e 006 5 0312e 009 280 672 178 335 126 177 1 32007e 015 122 366 4 46395e 014 190 612 165 634 11 sl 8 120 OK 1 77062e 006 1 13208e 006 3 18361e 006 2 8012e 010 348 614 185 112 194 119 1 67012e 015 119 428 4 34387e 013 265 863 168 572 115 16l 8 144 OK 1 84362e 006 1 49087e 006 4 23441e 006 6 01782e 010 370 111 203 634 197 094 4 29031e 016 117 395 4 05697e 013 282 753 218 605 11e ul 9 144 OK 5 69752e 006 2 35859e 006 4 13137e 006 2 8594e 009 542 377 291 9 28
3. Beam_Brk_Tension mdl Dz 1 6413e 006 Dy 1 6413e 006 e Bending 375 ee Beam with Brackets 2 RBE2 1 Beam Beam_Brk_Bending mdl Dx 7 08468e 005 Dz 7 08469e 005 2009 DRS Defense Solutions LLC Advanced Technology Center 376 MAESTRO 9 0 7 3 Refinement Top down auto refinement 11 5 Hydrostatic Balance This verification shows the comparison of MAESTRO s balance calculations as compared to theoretical calculations for a simple box model 2009 DRS Defense Solutions LLC Advanced Technology Center Verification and Validation 377 Models and Samples Verification Models Load Hydrostatic Balance box mdl poe Pitch Heel Pitch Heel 11 6 Second Flange The following second flange examples demonstrate the three methods for modeling a second flange the second flange strake defining a second flange on a beam and creating a T beam with a rod element as the second flange Example 1 2009 DRS Defense Solutions LLC Advanced Technology Center 378 MAESTRO 9 0 7 This example compares the displacement of a beam with a second flange a second flange strake a beam with a rod as the second flange and a rod with equivalent cross sectional area all subjected to a tensile force of 1 000 Newtons The intersection of all 4 elements is fixed and the opposite end of the beams frame and rod
4. ss issnennnnerensnnneennenneeennnnenneenenss 180 Loading The Model 186 Creating Groups sce ae orena aep aaa ea NU susteecaseebuede guste enceasuvetessduevensecsuvebesvenereeasces s 186 GrOUPS TOR E RE Re SE E a nn tte 197 Balancing the Model a a aia 202 Defining LOGS 5 55 55 AR EE dttones lie Mest tear hese 206 Creating A Load CASE a aa ara Re nee dues decd acy sce ae aea a AEEA EEN EAE EAAS PA 207 General TaD riria E a e a E a aaa te 208 MaSS Tab E E E AE A E E A oise nets ad is ce ace nn 208 Acc l ration Tab ysis cpiececieuicvinssceseveccdonsesceccennceduscsoddeseaneavecpenacedoates baysetestiecstacncviacarbabusudes cqousevacceavaandoseatersucbensees 216 End Moments Tab sicceiscccecavsdncsccsasaccccstenicdecsscsvascsnadsasunceataseveaivevtwadnainacaceabirdensd sodsdvetndsuaduccacadcennabadeadsdvasuechibusbedsoas 217 Pont Force TaD E E E E E 218 Pressure Tabi iscsscsssivcsceseccvacocescancsesecsasesvaesccencasaututedseausiecberiarsesiveduetndudecacarsducsveasevetndoudiuacddsubersdshdcdesavacessnusndveesne 218 Balance Pab aA E E E cabal sat hcesouasaspausensecunadncvseidedectdeussddbevesethsoueidath esunenvasuavaebaseveepiupuesersets 224 Constraint Tab oes iei sco 5a sss coi cease cece cic Aee a e e aAA VAEN EAE AAAA cece vev esti cone swodact aaae ara a Aea Ea Ere AA EEn AALE EEEE NEEE 225 Gorr sion Tab E e a a E a a EE 226 Analyzing and Post Processing 228 SOIVET LY oe E T ed een n rennes e nement net ue eee estate
5. 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 273 5 Choose the ALPS HULL analysis type This will automatically convert the existing strakes and stiffener layouts to the appropriate elements as described above and will generate the ALPS HULL analysis model and place it under the finemesh object the the Parts Tree Model Refinement FineMesh Module Name general group 001 Join Tolerance 00751667 in User Defined Module Origin optional in Default User Defined lt f mi pu Analysis Type TopDown Embedded N C Nastran Map Load Control E v Mesh Controls Minimum length along non stiffened edge in Minimum of segments between stiffeners H Convert beam frame girder web to Convert beam frame girder s flange to Cancel 6 Expand the finemesh object and right click on the ALPS HULL analysis model that was generated in the previous step Choose Add Mirror from the menu which will access the Mirror dialog Click OK 2009 DRS Defense Solutions LLC Advanced Technology Center 274 MAESTRO 9 0 7 File Tools View Model Groups Loads Hull Results Help Deh S62 Geaagaseulecss EPa T ITS K B alx finemesh Set Current Part Set View Part Set Current amp View Part oD PES Rename Copy Mirror Delete Set Visibiity On Set Visibility Off Visibility List Set Transpar
6. 2009 DRS Defense Solutions LLC Advanced Technology Center General 65 4 7 Existing groups can be combined and subtracted to create new groups using this dialog A new group of shared elements between existing groups can also be created 1 Move the groups of interest into the right column by clicking the group and then clicking the gt gt button 2 Select the operator for each group added this will add the elements of the selected group to the new group this will subtract the elements of the selected group from the new group amp this will add the shared elements of the selected groups to the new group 3 Select the group type from the drop down menu 4 Give the new group a name 5 Click Create Loads Menu The Loads menu allows the user to create or modify a load case as well as view the resulting pressure and forces for the selected load case A brief description of each option is discussed below Create Modify View Pressure View Mass View Point Load View Boundary gt Total Point Force Create Modify This option will launch the Loads dialog where load cases can be created modified and deleted View Pressure gt 2009 DRS Defense Solutions LLC Advanced Technology Center 66 MAESTRO 9 0 7 The sub menu allows the user to choose to view the pressure due to various loading options or all for the currently selected load case Note the s
7. top Origin Location Rotation Angles si x jo in X axis jo deg a DUG Y o in Y axis jo deg Z o in Z axis jo deg Create Modify Delete Close 10 Define the Origin Location and Rotation Angles for the module and click Modify Note these values are applied within the current part s reference system For example if your substructure X origin is set at 120 inches then setting the X origin of the module to 0 inches is equivalent to 120 inches in the global reference system 11 Select the Sections tab The default sections is 10 with 1 unit spacing Substructures and Modules E a General Location Sections Default Values top Add Index Spacing si B mi fri 5 Re space Remove Create Modify Delete Close 12 These sections can be re spaced or deleted and new sections can be created To do this highligh the sections and click Remove 13 Click Add and define the number of sections and their spacing Multiple sections can be added with different spacing 14 Click the Modify button 12 Select the Default Values tab 2009 DRS Defense Solutions LLC Advanced Technology Center 140 MAESTRO 9 0 7 5 5 Substructures and Modules E 4 x General Location Sections Default Values top Sections Bay 30 s1 B mi fri 5 Cylinder Length 0 in Jv Reference End Frame Opposite End Frame Create Modify Delete Close 13
8. 4 12 amp This icon allows the user to double click a triangle element and MAESTRO will automatically split the triangle into four triangles This icon allows the user to double click a triangle element and MAESTRO will automatically split the triangle into three quads This icon allows the user to double click a rod or beam element and MAESTRO will automatically split the rod or beam into two elements This icon allows the user to double click a beam element and MAESTRO will automatically split the beam element into two quads for the beam web and 2 quads for the beam flange if applicable This icon allows the user to double click a beam element and MAESTRO will automatically split the beam element into two quads for the beam web and 2 rods for the beam flange if applicable This icon allows the user to double click a beam element and MAESTRO will automatically convert the beam web to a quad and the flange to a quad if applicable This icon allows the user to double click a beam element and MAESTRO will automatically convert the beam web to a quad and the flange to a rod if applicable E This icon allows the user to merge two elements into one by clicking the first element and then double clicking the second element to be merged 4 This icon allows the user to double click a bracket element and MAESTRO will automatically convert the bracket to a triangle and a rod Standard Views MAESTRO has several d
9. Once a group is selected from the drop down menu click Add to add the tank group to the dialog The tank load can be defined three ways mass fraction of the volume filled or the pressure head measured parallel to the total acceleration vector from the point of lowest pressure to the point of highest pressure The fraction and head option will automatically calculate the mass weight of the tank using the given density The value of the mass fraction or head is entered into the Va ue column An optional value of the additional head measured as the height of fluid in a pipe for this volume can be added by entering a value into the Pipe Head column Using the fluid density of this volume MAESTRO will calculate and add a constant pressure throughout the volume The height is assumed as defined with no allowance for heel The Total Mass button will report the total mass of the defined volume groups based on their loading The CK OverFill will check that no tanks are overfilled based on the density and loading parameter Module Mass Mass that is not of the load carrying structure but whose spatial distribution approximates that of the structure is usually represented as a scaled version of the structural mass This offers the user a method to generate a specified amount of additional non structural mass and allocate it to a group of specific modules in proportion to their structural mass Here the user can add Scaled Mass groups
10. Tutorials 335 strakes within those modules for which we want to associate some module specific or strake specific constraint sets In this example we want to associate constraint set 3 the set containing the BBS gt 12 constraint that we just defined with strakes 2 and 3 of module 1 We identify these modules by means of the Group Dialog Box and the button for that is near the bottom of the Pre Processing Toolbar with a picture of thre stacked blocks amp Click on this to open the Dialog Box and you will see that one of the types of groups is the General group Click the General tab and then click the down arrow in the ID box and select group 1 This will fill the List Box with the two strakes of module 1 that constitute General Group 1 as shown in the following figure Groups Volume Plate Module Section Node Bay General Corrosion ID 001 v Name General Group 001 v Centerline Group MN Full Strake Full Compound Whole Module Select By Box Module Name top sub1 mod1 strake 3 top sub1 mod1 strake 2 Del tem Close To see how this group was defined let s make a second group using the following steps 1 Click the ID button to get the next ID number 002 2 Click the Full Strake Full Compound check box since we want to specify all of strakes 2 and 3 3 Click anywhere in the List Box and then move your cursor to the model and click on the two side strakes of the s
11. 4 16 Range When a view is selected with a legend of values this range is automatically populated with the maximum and minimum values The Min and Max can be overridden with user defined values by checking the Apply Defined Range box and inputting new numbers Corner Stress When this option is checked the stress contour plot is based on elemental nodal stress If it is unchecked the stress contour plot is based on the average elemental centroidal stress ALPS HULL If this option is checked it will put MAESTRO in ALPS HULL mode which will give additional right click functionality within the modeling space Auto Save and Recover Model Auto Save MAESTRO has an auto save function which will automatically backup the model after a set number of destructive commands A destructive command is any command where something in the model is created modified or deleted For example creating a strake or modifying a material property is considered a destructive command Changes to the graphics view i e model view orientation is not considered a destructive command To set the frequency of the automatic backup select File gt Autosave from the menu This will open the AutoSave Frequency dialog box AutoSave Frequency R Auto Save for every 5 destructive commands 2009 DRS Defense Solutions LLC Advanced Technology Center 120 MAESTRO 9 0 7 4 17 Input the number of destructi
12. 2009 DRS Defense Solutions LLC Advanced Technology Center 298 MAESTRO 9 0 7 Nastran Ansys Export Options Came Exportto Parts List is Naran C Ansys F Direct Input Stiffness Matrix Part Specification groups Load Case JALL v a C Lump Stiffeners Asbar C Triangulate Warped Quad E Launch Post Processor None C FEMAP Nastran Data File C Documents and Settings My Documents MAESTRO O The Parts List allows the user to select the part s or group s to export to the nas file To export the entire model select top Which parts or groups are to be exported is shown under Part Specification on the right of the dialog box FEMAP can be automatically launched once the file is created by clicking the radio button The Nastran data file is automatically given the same name as the mdl file and saved in the same location but can be changed by clicking the bution Modal Analysis 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 299 Nastran Ansys Export Options Options Parts List 63 top Export to Nastran C Ansys Direct Input Stiffness Matrix Part Specification PE Load Case ALL Structural Mass Matrix Consistent C Lumped External Shell Added Mass MFLUID Setting C MAESTRO Internal Tank Mass C MFLUID Smearto Skin Lump Stiffeners Asbar C Triangula
13. 4 Select the property of the stiffener from the drop down box If the property is not yet defined click the Property box and the Beam Property dialog will open 5 MAESTRO allows the user to define either the number of internal stiffeners or the Breadth between stiffeners Select the radio button for the option you desire and fill in the number of distance 6 MAESTRO also allows for an Edge 1 or Edge 2 stiffener The Edge 1 and 2 corresponds to a longitudinal stiffener layout applied to a strake In this case Edge 1 is the edge defined by EndPoint 1 and Edge 2 is defined by EndPoint 2 7 Click Create to save the stiffener layout This layout will now be listed in the drop down box in the Strakes and Quad dialog boxes 5 8 Importing Geometry Menu File gt Import gt Curves can be imported into MAESTRO to serve as construction geometry to assist in model generation The idea is to import curves at strategic locations such as the Reference and Opposite ends of the Parts definition This will allow the user to snap to these locations of interest using MAESTRO s construction geometry See the Construction Geometry section for more information on MAESTRO s construction geometry This tutorial shows the procedure for importing geometry as an IDF DXF or GF format 2009 DRS Defense Solutions LLC Advanced Technology Center 152 MAESTRO 9 0 7 5 9 1 Make sure that top is set to the current par
14. A load case consists of all of the loads which act on the structure at the same time Loads which do not act simultaneously should be placed in separate load cases unless their interaction is negligible Each load case produces a separate solution for the nodal displacements and hence load effects in the structure In the evaluation portion of MAESTRO for each possible limit state the solutions for all load cases are examined to find the worst case lowest adequacy parameter for that limit state A dynamic load case requires masses and accelerations The mass data is obtained by selecting any combination of masses and by adding properties that are specific to the intended load case The following figure presents the overview of MAESTRO s loading capabilities Load Case s EnA llinmante A nnanlarafinn a Daini Caran Dracairs mn afrainia End Moments Acceleration Paint Force Pressure Constraints Cuf Model The following subsections give more details regarding the Loads dialog Creating A Load Case General Tab End Moments Tab Acceleration Tab Mass Tab 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 207 Point Force Tab Pressure Tab Balance Tab Constraint Tab Corrosion Tab 7 4 1 Creating A Load Case The following tutorial shows the procedure for defining a load case 1 Begin by opening the loads dialog from the Loads gt Create Modify menu option
15. Creating Groups RCA CE Groups gt gt The groups dialog allows for the creation of 8 different types of groups New groups are automatically added to the parts tree under its appropriate heading Groups are often used to load the model as shown in the figure as well as for post processing A more detailed description and steps to create each group are below Volume Plate Module Section Nodal Bay General Corrosion Wetted Volume Group Tanks can be easily created in MAESTRO by defining a volume group by clicking the elements that make up the boundary faces of the tank This tutorial shows the procedure for creating a tank defined by a volume group 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 187 1 Begin by opening the groups dialog box using the Groups gt Volume menu option or from the toolbar Groups Volume Plate Module Section Node Bay General Corrosion g Name fT Centerline Group Full Strake Full Compound Select By Box Module Name eao Create Del ltem 2 Click the ID button to assign a unique ID to the tank 3 Type a descriptive name into the Name box 4 Check the Centerline Group if the tank spans the centerline of a half model This will automatically combine the mirrored group into one single group if the model is mirrored 5 Checking the Full Strake Full Compound box will include the entire st
16. Individual Panel Evaluation Hull Girder Collapse Legacy Version of MAESTRO Job Information This option will open the Job Information dialog Preferences This option will open the preferences dialog where background settings and DXF Import settings can be changed 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 Preferences Background Window Color Pattern gradientnorth w DXF Import Settings Number of Layers Number of Points Number of Curves Units This option will open the Units dialog Capture View gt This option allows the user to select to copy or save a screenshot of the modeler space view Print This option will open the Print dialog Print Setup This option will open the Print Setup dialog Quick Reference Files The next section of the File menu provides the previously opened model files for quick reference Autosave Frequency This option allows the autosave frequency to be changed 2009 DRS Defense Solutions LLC Advanced Technology Center General Recover Model This option will recover the model if a crash or other error occurs Exit This option will exit MAESTRO 4 3 Tools Menu 33 The tools menu provides several options to assist the user throughout the finite element analysis process A brief description of each option is discussed below Toolbars gt Construction Geometry
17. MAESTRO 9 0 7 7 3 Balancing the Model Menu Model gt Balance The following tutorial shows how to balance a coarse mesh model 1 Open the Hydrostatic Balance dialog from the Model gt Balance menu option or the toolbar Hydrostatic Balance Selection Convergence Criteria fe Auto Heave Force Gross Weight 0 001 c Heer Control Dz Between CG and CB Beam Cycles 10 px Between CG and CB LBL 0 001 Definition of Average Water Plane Center of Flotation Structure Coord Heel Angle Deg Trim Angle Deg All Load Cases 2 Check All Load Cases if you would like to balance all load cases otherwise only the currently selected load case will be balanced 3 Select Auto balance or User Control to define the model center of floatation or heel and trim angles 3 Click OK to balance the model The output tab will display the balance results for each load case 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 203 If a bending moment is applied to a cut model the MAESTRO balance command can be used to calculate the resulting shear force Balancing a Model in a Wave Wave heading Structu TR Relative wave HEADING angle The wave angle relative to the ship axis 8 60 L Ship length Wave length In the figure L a Wave amplitude x Wave axis always measured from the Reference Origin x Location of a wa
18. Gravitational constant G 32 1740 feet sec 2 9 80665 meters sec 2 Supported Symbols and Definitions ABT total area of transverse cross section of a bulbous bow Full port and starboard cross sectional area at the FP AM midship section area 2009 DRS Defense Solutions LLC Advanced Technology Center 400 MAESTRO 9 0 7 Immersed transverse sectional area located at MIDP APB planing bottom area Horizontally projected planing bottom area at rest excluding area of external spray strips Area outlined by the chine as projected onto a horizontal plane ATR total area of immersed transom Full port and starboard cross sectional area of a transom stern below the waterline AVL longitudinal area exposed to wind Area of portion of ship above waterline projected onto a longitudinal plane as viewed from the side AVT transverse area exposed to wind Area of portion of ship above waterline projected onto a transverse plane as viewed from ahead AW area of the waterplane Area enclosed by the outline of the waterplane AX maximum transverse section area Maximum immersed transverse sectional area BETD principal deadrise angle of planing bottom Angle of the tangent slope of the planing bottom For a temporary solution the tangent slope of the planing bottom at a point BPX 4 off the centerline located at the mid point of LPRC is recommended BETTR deadrise an
19. The Groups menu provides options to create modify and delete groups as well as perform operations on existing groups General Volume Plate Nodal Module Section Bay Corrosion Wetted Elements Operations General This option opens the groups dialog to the General tab Volume This option opens the groups dialog to the Volume tab Plate This option opens the groups dialog to the Plate tab 2009 DRS Defense Solutions LLC Advanced Technology Center 64 MAESTRO 9 0 7 Nodal This option opens the groups dialog to the Node tab Module This option opens the groups dialog to the Module tab Section This option opens the groups dialog to the Section tab Bay This option opens the groups dialog to the Bay tab Corrosion This option opens the groups dialog to the Corrosion tab Wetted Elements This option will create a general group named wet of all shell elements defined as wetted Operations This option will open the Group Operation dialog Group Operation New Group Name Type X general free edge check Group Name general free edge error volume fr65 73 centerline volume fr5 15 outboard volume fr15 21 outboard volume fr 65 73 outboard volume fr41 49 outboard volume fr33 41 outboard volume fr25 33 outboard plate deck winch node main engine general general group 003 volume volume group 008 qeneral wet ame _
20. 2 A dialog box will open asking the user if they would like MAESTRO to create a group of the elements with free edges and if MAESTRO should check for free edge errors If the user answers Yes to the first question a general group will be created and displayed with its free edges in red on the screen If the user answers No the entire model will be displayed with its free edges in red It is easiest to see the free edges in wireframe mode a with stiffeners and end points turned off 3 Select View gt Element Type from the menu to return to element type view Menu Tools gt Integrity Check gt Element Connectivity 1 This integrity check can be performed from the Tools gt Integrity Check gt Element Connectivity menu option 2 A dialog box will open reporting the number of unconnected elements if any 2009 DRS Defense Solutions LLC Advanced Technology Center 184 MAESTRO 9 0 7 3 If there are any unconnected elements they will be listed in the Output tab at the bottom of the screen 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 Loading The Model 186 MAESTRO 9 0 7 7 1 Loading The Model The topics in this section provide detailed information on the MAESTRO functionality used while loading the model for an analysis It describes the different methods for loading the model as well as options to graphically view the loads applied
21. MAESTRO has the ability to import a Nastran analysis model from File gt Import gt Nastran 2009 DRS Defense Solutions LLC Advanced Technology Center 234 MAESTRO 9 0 7 Import Nastran Data File Models and Samples system My Recent Documents My Network Files of type Nastran Input Files nas dat Cancel Select the nas or dat file to import and click Open A Nastran Import dialog will open allowing the user to set the module location and units Nastran Import Module Name finemesh sample Renumber Nodal and ElementiDs v m Module Location m Origin Location m Rotation Angles x i x axis o deg Y axis 0 deg Z axis o deg Units in Cancel This option will import the geometry and finite elements only and not the loads The model 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 235 8 3 can be synchronized to the global model using RSpline elements by right clicking on the new module in the parts tree and selecting Synchronize This will automatically place RSplines connecting the global model nodes with the imported Nastran model nodes Ship Motion smn For more information on importing a Ship Motion file please see the Importing Hydro Loads section Analyzing the Model Toolbar Menu File gt Analysis Evaluation gt Global FEA The following tutorial shows
22. e Comparison Tolerance tol Example cd system modeler90 exe ex1_maestro mdl maestro disp LC 1 2009 DRS Defense Solutions LLC Advanced Technology Center Advanced 315 FETAG 37 dt 0 001 tol 1 0E 6 Keyword stress Used to access the mid plane stress results of a given load case and fetag Note the user is to define via sub keywords the load case fetag type of mid plane stress and tolerance An example is provided below Sub keywords to stress e Load Case Specification LC e FeTag Specification FETAG e Mid plane Stress Type sxx syy syx e Comparison Tolerance tol Example cd system modeler90 exe ex1_maestro mdl maestro stress LC 1 FETAG 51 sxx 3518734 5 tol 0 01 9 2 Programming MAESTRO exposes the results file rlt through COM interfaces Two samples on written in C and one written in VC 6 are provided in the Models and Samples Advanced Programming directory MAESTRO also provides an example program in C that shows users how to compare 9 2 1 Read Results MAESTRO offers extensive post processing functionality However there are specific needs a user may have that is not included in the product To assist the user in extracting results MAESTRO exposes the results rlt file through a COM interface To use the MAESTRO COM interface successfully you need to understand e C C Programming e How to access the particular data Two sample programs are pr
23. mn 1 oa fF WN Part VI 1 2 Part VII O N a Part VIII 1 SateNet Network LOCK l TL peaareen aA aaan e ka t Aa Aaaa a aada aa Patara ran po Ee da enesenn 125 Installation Directory and Sample Files 126 Geometry Finite Element Modeling 128 Model Organization 5 23 22288 278 a e a aa ter tre nn net an eraa Dares Eoaea eedan ne 128 Defining Job Information ssssnnnnnennnnnneennnnnnennnnnnnnnnnee 134 Defining Units sian ne on A tn E ten lessons le nsn est en anne Eai 135 Defining Parts 258 8ss nd ES teens rceseneie renom rence ei entente entente 137 PartS Fr e 58 aura ie re SG ee nn ee te 7 140 Defining Materials amp Properties nsnnennnnnnnnnnennnnnennnnnnnes 143 Defining Stiffener Layouts ie nn un intl 149 Importing Geometry sssini enine aen aie ainiaan a aconta naasi aiai taaak uae aae aina Eion iuda ainega kini nite 151 Creating EndPoints amp Additonal NOdes nee 152 Creating Construction Geometry snmeneennnnnenennnnnenennns 154 Creating Oa O S aa a m ne em Mile nn le dieu esta ale Sanaan aS 157 Creating Additional Elements 159 Creating Compounds aee ea nn An dot lune an ias 167 Deleting Elements 4 aaa aana a E a aai 169 Mirroring a Mod l eison naana aAA aaan ANa EAA REA EEA A NAA AARAA 172 QUICK Creates n i a a aa aa aaaea arte a a aaa athe 173 Checking The Model 179 Defining Con stra Saa r r e en Oe Ae eaa raTa aeeaiei eee 179 Model Integrity Checks
24. 14 License amp Copyright MAESTRO Software License Agreement NOTICE PLEASE READ THIS LICENSE AGREEMENT CAREFULLY BEFORE INSTALLING OR USING THE SOFTWARE BY INSTALLING OR USING THE SOFTWARE YOU ARE AGREEING TO BE BOUND BY THE TERMS AND CONDITIONS OF THIS LICENSE AGREEMENT IF YOU DO NOT AGREE WITH THESE TERMS AND CONDITIONS PROMPTLY RETURN THE UNUSED SOFTWARE 1 RESTRICTED LICENSE This License Agreement grants you whether an entity or a person hereinafter referred to as the Customer the non exclusive non transferable perpetual right to use MAESTRO hereinafter referred to as the SOFTWARE for the stipulated License Fee 2 LICENSE RESTRICTIONS The SOFTWARE along with all security features shall be used only as stated herein Customer may not transfer or assign to another party or location the rights under this License Agreement the SOFTWARE or any accompanying Documentation without Licensor s prior written consent This license includes the right to use one copy of the SOFTWARE on any single computer provided the SOFTWARE is only used on one computer at a time The SOFTWARE is in use on a computer when it is loaded into temporary memory RAM or installed into the permanent memory of a computer e g a hard disk CD ROM or other storage device Customer may not use the SOFTWARE for commercial time sharing or rental use Customer may make one 1 copy of the SOFTWARE solely for backup archival or disaster
25. GRID COMPONENT COEFFICIENT GRID COMPONENT COEFFICIENT GRID COMPONENT COEFFICIENT ID NUMBER ID NUMBER ID NUMBER 17 L 1 000E 00 9 1 2 062E 01 9 3 3 088E 01 11 1 2 062E 01 13 1 1 753E 01 13 3 3 088E 01 15 i 2 062E 01 16 1 2 062E 01 17 2 1 000E 00 9 2 1 949E 01 11 1 1 177E 02 LL 2 2 097E 01 11 3 3 860E 01 13 2 1 761E 01 15 2 2 097E 01 16 1 1 177E 02 16 2 2 097E 01 16 3 3 860E 01 17 3 1 000E 00 9 3 2 000E 01 LL 3 2 000E 01 13 3 2 000E 01 15 3 2 000E 01 16 3 2 000E 01 17 4 1 000E 00 9 2 1 632E 04 Li 1 3 796E 04 ii 2 3 113E 04 EX 3 1 245E 02 as 2 7 706E 04 15 2 3 113E 04 16 1 3 796E 04 16 2 3 113E 04 16 3 1 245E 02 17 5 1 000E 00 9 1 1 992E 04 9 3 9 960E 03 aa 1 992E 04 13 1 7 968E 04 13 3 9 960E 03 15 2 1 992E 04 16 a 1 992E 04 17 6 1 000E 00 9 2 6 103E 03 11 1 4 890E 03 11 2 9 491E 06 11 3 3 796E 04 13 2 6 074E 03 15 2 9 491E 06 16 1 4 890E 03 16 2 9 491E 06 16 3 3 796E 04 Figure 1 MPC Definition from NEi Nastrain 2009 DRS Defense Solutions LLC Advanced Technology Center 380 MAESTRO 9 0 7 Figure 2 MPC Definition from MAESTRO 5 ID DOF 17 1 17 2 17 4 17 5 17 6 9 g 11 13 13 15 16 9 11 11 11 13 15 16 16 16 g 11 11 11 13 15 16 16 16 9 9 11 13 13 15 16 9 11 11 11 13 15 16 16 16 ONAENNO NAN RP WRF RP WRPUNRPNNWNRPNWNRPNNWNPNRP RP WP We Begin to assemble sparse matrix M ID DOF Coefficient gt RBE3
26. Node Plate Bay Add Total Mass Group Name Modify Del Row Close Help Once a plate group is selected from the drop down menu click Add The Mass column displays the previously defined mass and can be overridden here if desired The Total Mass button will report the the total mass of all the plate groups in the current load case Bay Mass The bay mass option is intended for large solid masses that are supported at several nodes and whose center of mass is an appreciable distance from these nodes Here the user can add Bay groups that were previously created using the Groups dialog to the current load case definition These previously defined bay groups are made available to the user via the drop down menu The default value of mass to be added can be overridden by another value if desired 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 215 LoadCase 002 Name General Mass Point Force Pressure Acceleration Volume Module Section Node Plate Bay starboard container Add Total Weight CK Tip Over BaySet Name Mass kg Delete Modify Del Row Close Help Once a bay group is selected from the drop down menu click Add The Mass column displays the previously defined mass and can be overridden here if desired The Total Weight button will report the the total weight of all the bay sets in the current load
27. Plate Module Section Node Bay General Corrosion D f x Name general group 001 T Full Strake Full Compound 7 Whole Module Module Name top sub1 mod3 frs31 40 strake Quad 4 2 top sub1 mod3 frs31 40 strake Quad 5 2 top sub1 mod3 frs31 40 strake Quad 1 2 top sub1 mod3 frs31 40 strake Quad 2 2 top sub1 mod3 frs31 40 strake Quad 18 2 top sub1 mod3 frs31 40 strake Quad 8 2 top sub1 mod3 frs31 40 strake Quad 6 2 I Select By Box 3 View the newly created general group by right clicking on the group in the Groups Tree If necessary modify the general group to capture all the elements participating in the progressive hull girder collapse analysis 4 Right click on the general group again and choose Refine from the menu This will bring up the Model Refinement dialog box shown below File Tools View Model Groups Loads Hull Results Help DSHS BMeaagsaseula Res ego tml 72 JTSB B URERRE PPP BRERASO 5 groups general B gei Pars Gc Le Bie gt Bee LV Rom x VORESG Enter required viewing angles 4 gt Command Output Grid setview angles Set View Part Set Visibiity On Set Visibiity Off Volume Pressure Context Default Color Context UserDef Color Free Edges Rename Copy Delete 1e Table Wet UnWet Fip Normal Eval Un Eval Do Undo Master Create Patch gt E Modiy
28. Set Transparency Off 4 a 4 pia A s is x 2i Select enter a menu or function setstd view portbow 2 The Hull Girder Progressive Collapse Analysis Setup dialog provides several user input fields Load Setup Select either a Hogging or Sagging scenario to be analyzed as well as define the number of incremental loading steps for the analysis The user can increase the number of incremental steps if complete hull girder collapse was not Bending The Vertical and Horizontal Rotation Increment represents the value at which each load step will be executed either in the Vertical Rotation or Horizontal Rotation plane Shear Force amp Torsional Moment The user can impose an initial Vertical Shear Force on the hull girder collapse analysis model Plate Initial Condition The user can impose known initial out of plane deformations or residual stress Stiffener Initial Condition The user can impose known initial out of plane deformations or residual stress 2009 DRS Defense Solutions LLC Advanced Technology Center 276 MAESTRO 9 0 7 Aluminum Heat Affected Zone The user can define the heat affected zone for aluminum structures 3 When all the parameters have been defined click OK When the analysis is complete i e all Incremental Loading Steps are done the user can begin to post process the results Hull Girder Progressive Collapse Ana
29. This icon launches a dialog prompting the user to select the existing modeler file they wish to open fl This icon will save the current modeler file over the existing file name If no file name is defined it will prompt the user to name the file and then save amp This icon will launch the print dialog allowing the user to print the a hardcopy of the contents of the main display This icon will launch the MAESTRO help file Pre Processing Toolbar The Pre Processing toolbar which is located on the left side of the interface provides fast and easy means of accessing the functions necessary to construct and load a finite element model i This icon launches the Job Information dialog It is the same as selecting File gt Job Information from the menu This icon launches the Parts dialog It is the same as selecting Model gt Parts gt Create Modify from the menu 2009 DRS Defense Solutions LLC Advanced Technology Center 100 MAESTRO 9 0 7 This icon launches the Materials dialog It is the same as selecting Model gt Materials from the menu 1 This icon launches the Properties dialog It is the same as selecting Model gt Properties from the menu This icon launches the Stiffener Layout dialog It is the same as selecting Model gt Stiffener Layout from the menu This icon launches the Reference Points dialog It is the same as selecting Model gt Nodes gt Create Mo
30. This option will provide the menu for the particular failure mode evaluation chosen during the analysis For more information on each adequacy parameter and how to perform a failure mode evaluation please see the Failure Mode Evaluation section 2009 DRS Defense Solutions LLC Advanced Technology Center 96 MAESTRO 9 0 7 List gt Elements Nodes Reaction Forces Elements This option will populate the Grid tab with a list of elements their stresses and adequacy parameter results if applicable The cells can be copied and pasted into a database program like Microsoft Excel if desired Nodes This option will populate the Grid tab with a list of the element nodes their location and their displacement The cells can be copied and pasted into a database program like Microsoft Excel if desired Reaction Forces This option will list the reaction forces and moments in the Output tab for each constrained node and total each force and moment direction at the bottom Export Output gt MS Excel Text File MS Excel This option will open the Output dialog so the user can select which properties and results to output MAESTRO will then automatically create a Microsoft Excel file of the selected output data 2009 DRS Defense Solutions LLC Advanced Technology Center General 97 Output Hull Girder Properties M Gross Weight Table M Buoyancy M Vertical Shear Force M Vert
31. again in order of increasing plate thickness As many lines are used as are required to input the total number of values specified by Item 2 of the first line The size parameter MPLTSZ defines the maximum number of allowable values All lines except the last line of plate thicknesses must have eight values LAST LINE ITEM 1 ITEM 2 ITEM 3 Roundoff fraction for the number of panel stiffeners STF When the fractional part of the number of stiffeners is greater than this value STFROF the number of stiffeners is rounded up to the next integer value For values less than STFROF the number is rounded down to the next lower integer The default value is 0 25 To switch off discretization of STF specify a value of 1 for this item Plate roundoff fraction PLTROF for the strake plate thickness and for the web and flange thicknesses of the stiffeners girders and frames For a thickness value TPL between discrete values T N and T N 1 the value of TPL will be rounded up to the value T N 1 if the ratio is greater than PLTROF and rounded down to T N if the ratio is less The default value is 0 25 To switch off discretization for plate thickness specify a value of 1 for this item Panel roundoff fraction PANROF for the web height HSW and flange breadth BSF of the panel stiffeners This item is used in a similar fashion to Item 2 except that the appropriate stiffener values are used instead of the plate thicknesses Th
32. cause translational displacement and moments will cause rotational displacement RSpline An RSpline element is used to model connections that are very stiff relative to the remainder of the structure Also the RSpline element can act as a boundary element when conducting a fine mesh model MAESTRO has three options for an RSpline element RSpline RBE2 and RBE3 RSpline Transmits displacements to a group of nodes located between the two defined reference nodes These translations are prescribed from the slope and displacement of a flexible tubular beam element connecting the two reference nodes This is the type of RSpline element used to transfer displacement from coarse mesh nodes to fine mesh nodes RBE2 Used to create a rigid body connection between a group of dependent nodes and one independent reference node An RBE2 element is usually used to model areas that are very stiff compared to the adjacent structure RBE3 Used to transmit motion between a group of nodes and one reference node The motion at the reference node is the least square weighted average of the motions at the other nodes An RBE3 element is used to transfer forces and moments from the reference node to several dependent nodes without adding stiffness to the structure 2009 DRS Defense Solutions LLC Advanced Technology Center 132 MAESTRO 9 0 7 Strakes and Modules Figure 3 below shows an example of a module which is a portion of stru
33. etc e How is a model balanced in MAESTRO How does this compare to Orca3D for example MAESTRO is a force based balance The equivalent forces are calculated for each panel element Orca3D however uses a volume buoyancy based balance e Can I hide particular substructures and modules Using a right mouse click on a particular Part via the Parts Tree the user has the ability to make particular parts visible or invisible This works well when you are turning the visibility of a few parts off but is a little inconvenient when turning many parts off When you are interested in turning the visibility off on of many parts substructures or modules use the Visibility List command which allows you to toggle the visibility on off of Parts quickly 1 Right click on any part in the Parts Tree 2 Choose Visibility List which opens a separate Parts Tree list 3 Left click on a part to toggle the visibility on or off This is especially useful when the model becomes sufficiently large and many parts exist e How do I model an l beam element MAESTRO can create an equivalent l beam element by adding a second flange to an existing T beam element This second flange is defined in the Beams tab of the Finite Elements dialog the Beam tab of the Compounds dialog or a second flange strake can be created The second flange is defined by a width and thickness Please see the Second Flange section under Verification and Validation for further dem
34. gt Create Modify gt Bracket from the menu This icon launches the Deletion dialog It is the same as selecting Tools gt Deletions gt Select from the menu amp This icon launches the Groups dialog It is the same as selecting one of the group types from the Groups menu This icon launches the Constraints dialog It is the same as selecting Model gt Define Constraints from the menu This icon launches the Loads dialog It is the same as selecting Loads gt Create Modify from the menu 2009 DRS Defense Solutions LLC Advanced Technology Center General 101 E This icon launches the Evaluation Patch dialog It is the same as selecting Model gt Evaluation Patch gt Create Evaluate from the menu Viewing Toolbar The Viewing toolbar which is located at the top of the modeling space provides the various viewing options for the model These options can be helpful from constructing the model all the way through post processing This icon launches the View Options dialog It is the same as selecting View gt Options from the menu This icon allows the user to click a part in the model space to set it as the current part It is the same as highlighting a part in the parts tree and right clicking and selecting Set Current Part or selecting Tools gt Set Current Part from the menu B This icon allows the user to click a part in the model space to set it as the current view It is the
35. loadcase 1 dx surge dy heave dz rx roll degree ry yaw degree rz pitch degree displacement 0 000 4 058 0 0 000 0 0 5320E 01 ax ay az arx rad sA2 ary rad sA2 arz rad sA2 acceleration T 2 3 0 0 000 0 0 1219E 01 W elm_ID pressure elmpressure elmpressure aby me elmpressure 12 3 loadcase 2 dx surge dy heave dz rx roll degree ry yaw degree rz pitch degree 4 058 00 0 displacement 0 000 0 0 0 0 5320E 01 ax ay az arx rad sA2 ary rad sA2 arz rad sA2 acceleration zi E 5 1 0 000 0 0 1219E 01 S elm_ID pressure elmpressure 18 0 20150E 05 elmpressure 19 0 14290E 04 elmpressure 21 0 02000E 05 For this example once the smn file is imported there are now two new load cases Each new load cases represents the the pressure loads from the smn file load cases and contains the external pressure defined on each element 2009 DRS Defense Solutions LLC Advanced Technology Center Advanced 317 Static Loads Hogging Wave Static Loads Sagging Wave ShipMotion Load Case 3 Options on Masses amp AcceleratShipMotionLoad Case 4 re Include structure s mass Self Weight Jv Include gravity V Floating Structure Ship etc F Additional acceleration End Moment Corrosion J User defined CG Re define constraints Natural freq analysis Create Modify Del Row Help These external pressure load cases can now be combined with existing load cases to acc
36. that were previously created using the Groups dialog to the current load case definition These previously defined scaled mass groups are made available to the user via the drop down menu In each load case a new value can be specified for the amount of mass to be added and this overrides the value given in the scaled mass group dialog 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 211 LoadCase Name General Acceleration Mass Point Force Pressure Balance Volume Module Section Node Plate Bay ightship st s lt sCs Add Total Mass Modify DelRow Close Help Once a module group is selected from the drop down menu click Add The Mass column displays the previously defined Mass and can be overridden here if desired The Total Mass button will report the the total mass of all the module groups in the current load case Section Mass In the design of long structures such as ships where overall bending is the dominant load effect the lengthwise distribution of mass must be accounted for early in the design and should be modeled as accurately as possible at all stages of the design Ideally in a three dimensional model the masses should be placed at their actual locations using whichever of the methods presented here volumes bays sets scaled nodal plate is most appropriate for each type of mass But at early stages of design som
37. 12 Strake Plates vy On aie Strake Frames JV On Scale Width Strake Girders V On Water Plane Width 1 Stiffeners Off Constraint Compounds F On onstraints 5 Quads F On Point Loads 0 Triangles Jv On Beams von Point Moments 0 REEE Iv On Markers a Springs M On RSplines F On Spring RSpline 1 Brackets VF On Apply Defined Range Blocks Pre Post processing Deformation Scale Range Tools amp View Style Corner Stress Off Viewports Video Driver Options des ALPS HULL Off Single Hardware 2 buffer Shrink Elements Split Vertical M Construction Geometry C Split Horizontal Advanced V Cutting Planes C Four Views World Axes F ae 5 Click OK when finished Individual element stresses for the defined range are now presented Elements that are outside of the user defined range are colored grey 6 To hide the elements outside of the user defined stress range click the icon Viewing Areas of Interest ropa Menu View gt Options The following tutorials shows how a user can post process a given area of interest This is useful when the analyst would like to isolate a particular area to view deformation or stress 1 After the results have been loaded click on the Result menu to open the drop down 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 253 menu Deformed Model Stress Adequacy gt List b
38. 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 287 Groups can be created within the fine mesh model and loaded in the load case dialog as with the coarse mesh model MAESTRO will automatically flag these groups as fine mesh and ignore them while solving the coarse mesh model The following example will walk through creating a simple top down fine mesh model 1 Begin by opening FineMeshStep0 mdl from the Models and Samples MAESTRO Installation directory 2 Create a general group of the middle 4 strake panels including the strake frames Volume Plate Module Section Node Bay General Corrosion Co J oor v Name General Group 001 117 Centerline Group Full Strake Full Compound Whole Module I Select By Box Module Name ID top ex1 sub1 mod1 strake Quad 9 3 top ex1 sub1 mod1 strake Quad 8 3 top ex1 sub1 mod1 strake Quad 8 2 top ex1 sub1 modi strake Quad 9 2 top ex1 sub1 mod1 strake Frame 9 2 mod1 strake Fi 3 Right click on the group in the parts tree and select Refine 2009 DRS Defense Solutions LLC Advanced Technology Center 288 MAESTRO 9 0 7 Model Refinement FineMesh Module Name 1e 005 m User Defined Module Origin optional m fe Defaut UserDefined Join Tolerance Analysis Type Top Down C Embedded Load Control ja ciate Jv Map Loads Mesh Controls Minimum lengt
39. 7 2 Change the radio button in the method frame to the desired evaluation method How do you evaluate an individual element 1 Open the Limit State Creation Evaluation dialog box 2 Place the cursor in the patch ID drop down box 3 Use the mouse to select an element 4 Modify the geometry and load parameters if necessary 5 Click Compute button How do you define a patch without building a model 1 Open the Limit State Creation Evaluation dialog box 2 Click the ID button 3 Change the radio button from Auto to User defined 4 Enter the desired data 5 Click Create How do you view the element evaluation flag From the main menu click View gt Patches gt Element Evaluation How do you turn an element evaluation flag on or off 1 Query a Patch 2 Right click and select Evaluation Off How do you remove a patch 1 Query a patch 2 Right click and select Remove How do you define the Ultimate Strength Parameters Applies to ULSAP evaluation method 1 From the main menu select Model gt ULSAP Parameters 2 Click the ID button Enter proper values for the ULSAP ultimate limit state parameters and click Create Note the default ultimate limit state parameters will be automatically applied to any patch which is not specifically associated to a set of ultimate limit state parameter 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzi
40. Check gt Warped Quad menu option 2 Adialog box will open allowing the user to set the maximum allowable quad warping in degrees the default is 20 0 3 If there are no warped quads in the model a dialog box will notify the user of this otherwise the quad exceeding the warped angle will be identified with a color corresponding to the warped angle as defined in the legend on the right of the screen All other elements will be gray 2009 DRS Defense Solutions LLC Advanced Technology Center Checking The Model 183 4 Select View gt Element Type from the menu to return to the element type view Toolbar N A Tools gt Integrity Check gt Overlapped Elements 1 This integrity check can be performed from the Tools gt Integrity Check gt Overlapped Elements menu option 2 If there are no overlapped elements in the model a dialog box will open notifying the user of this otherwise the overlapped elements will be grouped and shown on the screen 3 A dialog box will open asking if the user would like to use the deletion dialog box to delete the overlapped elements It is recommended that the user investigate further to determine which is the true overlapped element before deleting 4 Select View gt Element Type from the menu to return to the element type view RE iew gt Edges gt Free Edges 1 This integrity check can be performed from the View gt Edges gt Free Edges menu option
41. Cutting Planes only alters the view on the display it does not actually change the model The user can add any number of cutting planes to the model and they are stored with the particular part in which they are defined Cutting planes do not persist in the model if it is saved and retrieved 2009 DRS Defense Solutions LLC Advanced Technology Center General 121 YZ Plane ZX Plane XY Plane YZ Slice ZX Slice XY Slice Specify Delete Places a cutting plane in the YZ plane YZ Plane issues a prompt to specify first a point on the cutting plane and second a point on the visible side of the cutting plane These points may be specified by clicking on a point in the modeling space or entering the coordinates in the form of x y z at the command line Places a cutting plane in the ZX plane ZX Plane issues a prompt to specify first a point on the cutting plane and second a point on the visible side of the cutting plane These points may be specified by clicking on a point in the modeling space or entering the coordinates in the form of x y z at the command line Places a cutting plane in the XY plane XY Plane issues a prompt to specify first a point on the cutting plane and second a point on the visible side of the cutting plane These points may be specified by clicking on a point in the modeling space or entering the coordinates in the form of x y z at the command line Erases everything f
42. DRS Defense Solutions LLC Advanced Technology Center 46 MAESTRO 9 0 7 3 Edges This option checks the model for edges where 3 elements meet and can create a general group of the 3 edge elements if desired It is easiest to see the edges in red when the model is in wireframe view 4 or More This option checks the model for edges where 4 or more elements meet and can create a general group of the 4 or more edge elements if desired It is easiest to see the edges in red when the model is in wireframe view Patches Element Evaluation Patch Element Evaluation This option will display the elements that make up the patches that will be evaluated This includes single panel elements that are bordered by beam elements The dynamic query icon 7 with patch checked can be used to highlight an element or patch and select Evaluation Off 2009 DRS Defense Solutions LLC Advanced Technology Center General 47 Patch This option will display the defined patches for the model They dynamic query icon Lhd can be used to highlight a patch and retrieve information about it by clicking the icon and selecting Patch from the drop down menu Plate Element Normal Side Element Pressure Side Stiffener Side Offset Element Normal Side The figure below shows how MAESTRO distinguishes between a positive normal and negative normal face The pink face of the element will re
43. Export Output gt Contour 2 Click on Stress and select which stress to display resurs IES Deformed Model 5 m s v 48 v Mid X Normal Adequacy Mid Y Normal Plate Mid XY Shear Plate Mid Von Mises List Export Output gt Top g Bottom Beam gt Contour Directional Define Direction Show Direction A detailed description of each type of stress that can be recovered can be found in the Stress Results sections 3 Click on the View Options icon or select View gt Options from the menu 4 From the View Options dialog see below click the Apply Defined Range checkbox This will enable the Min and Max Range fields for the user to define the stress range of interest 2009 DRS Defense Solutions LLC Advanced Technology Center 254 MAESTRO 9 0 7 8 9 View Options Labels amp Entities Visibility Plot Legend EndPaints Off Master Elements v On Fonts sans serif Additional Nodes Off Plate Offset Tr of Color white Strake Labels 7 Of Water Plane off F 12 Strake Plates vy On aie Strake Frames JV On Scale Width Strake Girders V On Water Plane Width 1 Stiffeners F Off Constraint Compounds F On onstraints o Quads F On Point Loads 0 Triangles M On s AE TA Cii Point Moments 0 Riek Iv On Markers 2 Springs lv On RSplines F On Spring RSpline 1 Brackets VF On Apply Defined Range Blocks Pre Post processing De
44. Model gt Materials menu or from the toolbar Material Name Grade A Steel v ID 100002 Y Type lsotropic x Name Value Young s Modulus Ex N m 2 2 04e 011 Poisson Ratio 0 3 Density kg m 3 7850 Yield Stress N m 2 2 35e 008 Ultimate Tensile Strength N m 2 4e 008 Reduced Yield Stress at AL Heat Affected Zone N m 2 2 35e 008 Weld Residual Stress Yield Stress 0 Structural Proportional Limit Ratio 1 2 Click the ID button to get the next unique ID for the new material 3 Type in a descriptive Name for the material and select the type Isotropic Orthotropic or Compound 4 Fillin the material parameter values in the units specified 5 Click the Create button This procedure can be repeated to create additional materials It can be helpful to create all the anticipated materials prior to creating the model 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 145 Toolbar Menu Model gt Properties gt Once a material s is defined the Properties dialog box is used to create Plate Beam Rod and Spring element properties Begin by opening the Properties dialog box from the Model gt Properties gt menu or from the toolbar Properties Plate Beam Rod Spring Identification Name v ID pooot X Laminate Failure Criteria Failure Theory vy Allowable Interlaminar Shear Stress N m 2 T
45. Otherwise MAESTRO will automatically calculate these values 6 Click Create This procedure can be repeated to create additional bracket elements For more information on brackets see the Bracket Verification section 5 13 Creating Compounds Menu Model gt Elements gt Create Modify gt Compound Compound elements provide a convenient method for quickly creating repetitive transverse structure Compounds are made up of spring rod beam and plate elements A prototype is created once and can be repeated along a module s longitudinal direction using the replication rule This tutorial shows the procedure for creating a compound prototype and setting the replication rule 1 Begin by opening the Compounds dialog box using the Model gt Elements gt Create Modify gt Compound menu or from the toolbar 2009 DRS Defense Solutions LLC Advanced Technology Center 168 MAESTRO 9 0 7 Compounds _ ER E Spring Rod Beam Tri Quad Bracket Rule si Add Modify Remove Connectivity Node 1 Node 2 Property Property v ID se Create Cmpd Modity Cmpd Jelete Cmpd Close 2 Make sure the appropriate module is set as the current part and click the ID button at the top of the dialog to assign a unique ID to the compound 3 Type in a descriptive name for the compound in the Name box and click Create Cmpd 4 Create Springs Rods Beams Tris and Quads that make up the comp
46. Part 252 227 7014 a 5 and used in 48 C F R Part 12 212 and 48 C F R Part 227 7202 as applicable Consistent with 48 C F R Part 12 212 48 C F R Part 252 227 7015 48 C F R Part 227 7202 1 through 227 7202 4 48 C F R Part 52 227 19 and other relevant sections of the Code of Federal Regulations as applicable the Commercial Computer Software and Computer Software Documentation are distributed and licensed to U S Government end users a only as commercial items and b with only those rights as are granted to all other end users pursuant to the terms and conditions herein MISCELLANEOUS If any portion of this License Agreement shall be held to be illegal or otherwise void and invalid the remaining portion of the License Agreement shall not be affected and it shall remain in full force and effect This License Agreement constitutes the exclusive and entire understanding between Licensor and Customer with respect to the SOFTWARE This License Agreement supersedes any prior proposals bids quotes representations agreements or any other understandings whether oral or written regarding the SOFTWARE or the relationship between Licensor and Customer and may only be modified by a written agreement executed by authorized representatives of both parties Licensor hereby rejects any additional or inconsistent terms and conditions offered by Customer at any time and irrespective of Licensor s commencement of performance or shipment or the acce
47. SHIFT gt or lt CTRL gt acceleration Pan lt SHIFT gt drag Spin drag Main display quick view menu Main display lt CTRL gt quick construction geometry menu Parts Groups tree quick menu Command line Output window Grid window quick menus Select menuitoolbar items Selectedit elements nodes and parts Left Mouse Button The left button is used to select any menu item toolbar item parts tree item and groups tree item The left button is also used to interact with MAESTRO s many dialog boxes In conjunction with Finite Element Reference Points Compounds and Strakes dialog boxes the user can select the closest entity It is important to note that the user must first click in the ID field of the dialog box to select the entity of interest Right Mouse Button The right button is used to invoke various quick access menus The quick access menu will differ depending on where the cursor is located in the GUI Main Display Area When the mouse cursor is located in the main display area the user with the click of the right button will access the menu shown below This menu item allows the user to set the current view projection Here the user can choose from a list of viewing operations and standard views This menu also allows the user to toggle a perspective projection on or off as well as copy the current display 2009 DRS Defense Solutions LLC Advanced Te
48. Solutions LLC Advanced Technology Center 68 MAESTRO 9 0 7 View Mass gt This sub menu allows the user to view the different mass loads that may be imposed on the model for the currently selected load case Volume Module Nodal Plate Bay Volume This option will display the volume groups that are loaded for the currently selected load case Module This option will show the modules and their corresponding elements which are added to the load case either as a structural weight or a scaled weight for the currently selected load case Nodal This option will display the nodes which are applied a mass in the currently selected load case View Point Load This option will give a graphic representation of the directional load applied at each node s 2009 DRS Defense Solutions LLC Advanced Technology Center General 69 The dynamic query th selected node icon can be used to query the force in each direction at the View Boundary Note this option is for cut models only Vertical Bending Vertical Shear Horizontal Bending Horizontal Shear Torsion All Vertical Bending This option will graphically display the boundary nodal forces and moments applied to fie simulate the user defined vertical end moments The dynamic query icon can be used to query the force and moments at individual nodes Vertical Shear This option will graphically display the bounda
49. View Longitudinal Torsional Moment command toggle the Dynamic Query icon and move the mouse cursor over a particular portion of the graph This will produce a text box with graph data Further the user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph entity of interest 2009 DRS Defense Solutions LLC Advanced Technology Center General 79 Torsion Moment lbf in 6 81E 010 010 5 94E 010 5 51E 010 5 07E 010 4 63E 010 4 20E 010 3 76E 010 010 ni ESRI mine 2 89E 010 246E 010 2 02E 010 1 59E 010 1 15E 010 7 15E 011 2 80E 011 1 56E 011 Element Effectiveness The View Longitudinal gt Element Effectiveness command under the hull menu shows a graphical representation of which elements have longitudinal effectiveness The Dynamic Query Lhd function can be used to highlight an element and toggle on or off whether the element is longitudinally effective 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 80 h WAY V p LL LEE a N77 be All Sections The View Longitudinal gt All Sections command under the Hull menu will display all the sections of the model This is helpful if you are viewing specific sections and would like to return to the full model view 2009 DRS Defense Solutions LLC Advanced Technology Center General 81
50. Yes If it asks about overwriting the ex2 rlt file say Yes always This loads the results into the Modeler so that the Modeler can display them graphically However most of the results of an Optimization Job are text and tables rather than graphics and so we first want to look at the output file ex2 out In the Main Menu click on Edit and then on Maestro Out The output file consists of pages although they are not separated it is one continuous file Each page starts with two lines containing the Job Title and other information with the page number at the far right Page 20 of the output shows the initial design variables The flange breadth of the frames and girders is set to the minimum value required to avoid lateral buckling Here again the aim is to make the initial design be a typical good rulebased design which fulfills the requirements but not to excess 2 10 1 Initial Adequacy Parameters Strake Level After the finite element analysis MAESTRO s next major task is the evaluation of all of the strakes calculating the 33 strakebased limit values combining these with the actual values to obtain the adequacy parameters and then for each limit state and for each strake searching through all bays and all loadcases to find the worst lowest 2009 DRS Defense Solutions LLC Advanced Technology Center Tutorials 339 value of each adequacy parameter The program then prints these lowest values
51. adequacy parameter values for some nonfailure constraints The area constraint is the requirement that the strake crosssectional area be at least as large as the value that is determined by the module level optimization in which the design variables are the strake areas Since module level optimization has not yet occurred this constraint is not yet relevant The other columns in that table are not used in this example 2 10 2 Initial Adequacy Parameters Module Level After the strake evaluation the program then evaluates the limit states at the module level 1 PCMY Panel Collapse Membrane Yield As shown earlier page 21 of the output the initial design satisfies the PCMY constraint for both deck and bottom Since this constraint actually belongs to the module optimization problem the PCMY adequacy parameters are printed again on page 25 including in this case the values for the side strakes The value of 0 2706 for the deck and bottom shows that their von Mises stress even after being multiplied by 1 5 is well below the yield value 2 Minimum Required Moment of Inertia 2009 DRS Defense Solutions LLC Advanced Technology Center 340 MAESTRO 9 0 7 In this example the required value is 3 0x10s ins On page 19 of the output the actual value is shown to be 1 209x106 and therefore on page 25 the adequacy parameter is well above zero being 0 602 3 Minimum Required Section Modulus In this examp
52. also be achieved dynamically through the dynamic rotation toolbar button This icon will toggle the view of the Parts Tree on or off a v 7 This icon allows the user to select an element type to apply the Quick Create functionality to This icon is for the Cancel command Clicking on this toolbar button will cancel any action that is currently being executed and also clears the command stack This is the same as pressing the Esc key tB This icon allows the user to query the model dependent on the current view by moving the mouse cursor over an element Post Processing Toolbar The Post Processing toolbar which is located at the top of the modeling space provides quick access to functions to balance analyze and post process the model LoadCase Ov This drop down menu allows the user to quickly switch between defined load cases and also shows which load case the current results shown are for 2009 DRS Defense Solutions LLC Advanced Technology Center General 103 T This icon launches the Balance dialog It is the same as selecting Model gt Balance from the menu N This icon toggles the Contour results plot on and off This icon is used with composite layers analysis amp Y This icon launches the Animation dialog It is then used to toggle the animation on or f O This icon launches the Analysis dialog Clicking the drop down arrow allows the user to select the a
53. arc 90 degrees thickness 0 1 E 1 0e v 0 25 mesh 6x 1 BCs Loads JMAESTROJTheoreticalMAESTRO MSC _ Input Data Solver Error Quad4 Files Error Clamped Unit force curvedbea in v 0 0880 v 0 0873 0 8 0 8 m mdl Y direction curvbb nas curvbb mo d curvbb f06 2009 DRS Defense Solutions LLC Advanced Technology Center Verification and Validation 363 11 1 4 11 1 5 curvedbea u 0 4492lu 0 5022 10 5 4 9 m mdl curvbs nas curvbs mo d curvbs f06 Twisted Beam The fourth test is the twisted beam problem The size of the beam element mesh and material properties are given in Figure 1 The purpose of this test is to study the ability of an element to treat the coupling of in plane and out of plane strain when there is a warped element mesh In this test the warp of each element is 7 5 degrees As shown in Table 1 the MAESTRO QUAD4 gives results that are in good agreement with theoretical results Figure 1 Twisted Beam Length 12 0 Width 1 1 Depth 0 32 Twist 90 degrees E 2 9e 7 v 0 22 mesh 12x 1 air MAESTRO heoretical Een Input Data Solver Error Files Out of Pla Clamped Unit Force In Plane Shear Jat one end of the beam Table 1 Twisted Beam Results Rectangular Plate Under Lateral Load The fifth test investigates the accuracy of the plate elements bending response for the case of a rectangular plate A lateral load is applied to a r
54. are constrained such that only axial motion is allowed This model SecondFlangeTension mdi can be found in the Program Files MAESTRO Models and Samples Verification Models Second Flange directory Beam with second flange F 1000 N D 1 08948e defined D Second flange strake F 1000 N y 1 08948e Rod with equivalent cross F 1000 N D 1 08948e sectional area Beam with rod defined as F 1000 N Dy 1 08948e second flange Example 2 Y Z X 2009 DRS Defense Solutions LLC Advanced Technology Center Verification and Validation 379 This example compares the deformation of a beam with a second flange defined and a second flange strake under a lateral load The ends of both beams are fixed and a later load of 1000 N is applied at each beam s center This model SecondFlangeLateral mdl can be found in the Program Files MAESTRO Models and Samples Verification Models Second Flange directory Beam with second flange F 1000 N D 5 70311e7 defined Second flange strake F 1000 N D 5 70311e7 11 7 RBE3 RBE3 implementation was compared to NEi Nastran The results of the two multipoint constraint coefficients are provided below The MAESTRO model RBE3 mdl and the related NEi Nastran files can be found in the Program Files MAESTRO Models and Samples Verification Models RBE3 directory MED SF F BOE BT CONSTRAINT DEFINITION DEPENDENT DEGREES OF FREEDOM INDEPENDENT DEGREES OF FREEDOM
55. as Dynamic Design Analysis Method DDAM e How do eliminate local distortion of boundary modules when applying end moments End moments applied in MAESTRO are simply a combination of end nodal forces that collectively sum to the user defined moments Unless additional local structure for example a transverse bulkhead is applied we would expect to see local deformation 12 4 Licensing and Security Device e How do I transfer my license to another computer MAESTRO licenses can be easily transferred between computers with the USB security device Before plugging the security device into the new computer verify that MAESTRO has been installed After this the security device can be plugged into the new computer and MAESTRO can be launched Security drivers and network servers are integrated into the MAESTRO installation process Therefore if MAESTRO version 9 0 or newer is installed licenses can be moved between computers by simply moving the security device e How do I renew my maintenance and support contract or add modules to my license To renew your maintenance and support contract or to add additional modules to your license please send an email to sales orca3d com with your contact information license number and request for update or addition and you will receive a quote for these services e have installed MAESTRO 9 0 or newer why doesn t my Sentinel System Driver and Protection Server show in the Add Remove Programs dial
56. as a tool to match a known weight distribution 1 Begin by opening the groups dialog box using the Groups gt Module menu option or from the toolbar Groups Volume Plate Module Section Node Bay General Corrosion ID v Name v Mass kg Add Whole Ship Module Name Color Create 2009 DRS Defense Solutions LLC Advanced Technology Center 190 MAESTRO 9 0 7 Click the ID button to assign a unique ID to the module group Type a descriptive name into the Name box gt A N Click in the white space and then click on the module s to add to the group 5 Assign the modules a scaled mass weight value This mass weight is assumed to be symmetric and should be a half value for half width models Note the field is dependent on the Units used Mass when working with SI Units or Weight when working with fps mks cks and ips Units 6 The Add Whole Ship option can be clicked to add all modules In this case the mass weight assigned to these modules is the full value regardless of whether the modules are a half ship 7 Select a color from the drop down menu to give the module group a unique color 8 Click the Create button The new module group will appear under the group tab of the parts tree under the module folder as the name given in the Groups dialog box Section Group In the design of long structures such as ships where overall bending is the dominant l
57. button and moving the mouse to pan the model Rotate This option allows the user to rotate the model with the mouse This can also be done by clicking and holding the mouse wheel button and moving the model as desired Zoom gt 2009 DRS Defense Solutions LLC Advanced Technology Center General 39 Zoom Window In Zoom Window Out Zoom Extents Zoom Window In This option will allow the user to select an area of the model by a user defined box and zoom in This can also be done by right clicking in the model space and selecting Zoom In Zoom Window Out This option will allow the user to select an area of the model by a user defined box and zoom out This can also be done by right clicking in the model space and selecting Zoom Out Zoom Extents This option allows the user to select to zoom to the extents of the model This can also be done by right clicking in the model space and selecting Fit Set View gt Body Plan Profile Plan SouthEast SouthWest NorthEast NorthWest Specify Store Recall Named View v Perspective This option allows the user to select from the standard views or a named view Set View Style gt Nodes On Off Shrink v Solid Wireframe This allows the user to change the view between a black or white background if current background is black or white show nodes on or off shrink or unshrink elements and solid or wireframe view These options can al
58. data The user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph entity of interest 2009 DRS Defense Solutions LLC Advanced Technology Center 72 MAESTRO 9 0 7 Self Weight lbf 1 43E 002 2 94E 003 3 88E 003 4 81E 003 7 61E 003 8 54E 003 9 47E 003 1 04E 004 1 13E 004 1 23E 004 1 32E 004 141E 004 1 51E 004 View Gross Weight The View Gross Weight command under the the Hull menu is used to display the FE model s gross weight for the selected load case As shown below MAESTRO produces a display of this weight distribution Further MAESTRO echoes this distribution to the Output window which is found at the bottom of the MAESTRO GUI In conjunction with the View Gross Weight command the user can use the Dynamic Query tool which can be initiated via the LM icon to query the distribution graph To use this functionality the user must select the View Gross Weight command toggle the Dynamic Query icon and move the mouse cursor over a particular portion of the graph This will produce a text box with graph data The user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph entity of interest 2009 DRS Defense Solutions LLC Advanced Technology Center General 73 2 94E 003 3 88E 003 4 81E 003 7 61E
59. down and set the model to deformed view from Results gt Deformed Model The different mode shapes can be selected by right clicking in the model space and selecting the frequency from the menu Define Range From List Frequencies Dry Mode 1 Freq 1 91552 Hz Dry Mode 2 Freq 4 42245 Hz Dry Mode 3 Freq 5 46258 Hz Dry Mode 4 Freq 6 65014 Hz Dry Mode 5 Freq 10 8164 Hz Dry Mode 6 Freq 11 691 Hz Dry Mode 7 Freq 11 7666 Hz Dry Mode 8 Freq 13 5731 Hz Dry Mode 9 Freq 13 6828 Hz Dry Mode 10 Freq 13 8431 Hz LR on ag e SSSR ES 2009 DRS Defense Solutions LLC Advanced Technology Center 240 MAESTRO 9 0 7 8 5 Stress Results For a detailed description of the stresses recovered for each element type click one of the quick links below Rod Beam Bare Plate Stiffened Panel 8 5 1 Rod The axial stress of rod elements will be displayed when Mid Normal X and Mid Von Mises are selected from the Results menu 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 241 top s2 midbody m2 fr49 63 Rod 3 SigX 1 6444E 003 The dynamic query icon ty can be used to highlight a rod element and recover the axial stress Double clicking the element will echo the results to the Output tab Rod elements will be grayed out when stress options other than the two listed above are chosen However the axial stress can still be recovered from a rod element
60. e See the Tutorials section for some basic tutorials to get you started with using MAESTRO e You will find some of the models used in the tutorials in the MAESTRO Models amp Samples Tutorial Models folder e Full ship sample models can be found in MAESTRO Models amp Samples Full Ship Models folder Getting a printed user manual Please don t try to print the HTML Help version of the help from the Microsoft help viewer it would look terrible You will find a formatted PDF version of the entire documentation designed for printing in the MAESTRO Help folder or from Start gt All Programs gt MAESTRO 9 0 gt Email Support maestrosupport orca3d com Telephone Support 410 604 8000 Website www orca3d com maestro Forum MAESTRO Forum Other MAESTRO Representatives In addition to the options above you may also contact a local representative from the list below for MAESTRO technical support Europe Middle East Russia Design Systems amp Technologies Phone 33 4 92 91 13 24 2009 DRS Defense Solutions LLC Advanced Technology Center 22 MAESTRO 9 0 7 3 3 3 4 Fax 33 4 92 91 13 38 ds t ds t com Japan SEALS Ltd Phone 81 45 895 6051 Fax 81 45 895 6052 uenoman mbd sphere ne jp How to buy MAESTRO MAESTRO can be purchased by visiting the online purchasing page and filling out the required information and submitting the form Once the form is received you will be c
61. for free free or partially restrained systems Maximum number of iterations allowed Static Condensation Under the Job Type section MAESTRO can perform an analysis for the structure vibrating in vacuo or in fluid When Wet Mode is selected the added mass of the seawater is automatically applied to the wetted elements MAESTRO offers three iterative solver methods Subspace Inverse Power and Lanczos A Sturm Check can be applied to check for multiplicities of the calculated eigenvalues The user can input the number of natural frequencies to compute the eigenvalue tolerance for the iteration solver and the shift in hertz for free free or partially restrained systems The maximum number of iterations may need to be increased if the convergence is slow the default value is 999 The natural frequency analysis load case will be solved during the coarse mesh analysis The Output tab will display a summary of the natural frequencies calculated during the analysis 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 239 Mode 1 is converged Number of iterations 6 Freg 1 91552 Hz Mode 2 is converged Number of iterations 19 Freg 4 42245 Hz Mode 3 is converged Number of iterations 3 Freg 5 46258 Hz Mode 4 is converged Number of iterations 3 Freg 6 65014 Hz Mode 5 is converged Number of iterations 24 Freq 10 8164 Hz Mode 6 is converged Number of iterations 2
62. geometry of the structure As will be shown later this occurs in the present example Also some of the results may be different to what was anticipated perhaps leading to the realization that a load has been forgotten or that another constraint is needed As will be shown MAESTRO s restart feature makes it relatively easy to make such changes without having to start all over from the initial design In the present case there are no unusual changes and the results are quite satisfactory The objective function and its ingredients cost and weight have decreased Compared with the original value 1 000 on page 20 the new value 0 830 on page 29 shows a 17 improvement Figure 1 the numbered figures are at the end of the text just before Appendix A gives a plot of the objective cost and weight for all of the cycles that we will be doing 2 12 Subsequent Design Cycles And Evaluation Cycle The program now begins the second design cycle first performing a new finite element analysis then a new evaluation at both strake level pages 30 to 33 and module level page 34 then a module level optimization 35 and finally the strakebystrake re evaluation and optimization which is not printed The active constraints are given on page 36 and the results are given on page 38 The objective function is now 0 790 As requested in the Job Information data the program next performs a third design cycle pages 39 to 47 The objective functi
63. groups are made available to the user via the drop down menu The default value of total mass to be added can be overridden in this dialog 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 213 LoadCase v Name General Acceleration Mass Point Force Pressure Balance Volume Module Section Node Plate Bay v Add Total Mass Nodal Group Name 3 Modify Del Row Close Help Once a node group is selected from the drop down menu click Add The Mass column displays the previously defined mass and can be overridden here if desired The Total Mass button will report the the total mass of all the node groups in the current load case Plate Mass The Plate mass option offers the user a method to generate a specified amount of additional non structural mass and allocate it equally among each plate element that defines the plate group Here the user can add Plate groups that were previously created using the Groups dialog to the current load case definition These previously defined plate groups are made available to the user via the drop down menu The default value of total mass to be added can be overridden by another value 2009 DRS Defense Solutions LLC Advanced Technology Center 214 MAESTRO 9 0 7 LoadCase x Name General Acceleration Mass Point Force Pressure Balance Volume Module Section
64. name into the Name box 4 Click in the white space and then click on the module s to add to the group Clicking any element of a module will add the entire module to the group If the Module all sections box is checked when a module is added it s mass weight per length will apply to all sections of that module 5 Define the mass weight per length for each section or entire module The mass will automatically update based on the length of the section 6 Select a color from the drop down menu to give the section group a unique color 7 Click the Create button The new section group will appear under the group tab of the parts tree under the section folder as the name given in the Groups dialog box 2009 DRS Defense Solutions LLC Advanced Technology Center 192 MAESTRO 9 0 7 Node Group A node group is used to define an additional mass which is equally divided among a collection of nodes The nodes may be of any type endpoint generated or additional and can be located anywhere in the model 1 Begin by opening the groups dialog box using the Groups gt Node menu option or from the toolbar Groups Volume Plate Module Section Node Bay General Corrosion v Name Mass 0 kg Centerline Group All visible nodes in the section Module Name Color Create Del Item Close 2 Click the ID button to assign a unique ID to the node group 3 Type a descriptive name into
65. only available for General groups Wet Unwet This will toggle the plate elements of the highlighted general group as wet or unwet Flip Normal This will flip the normal direction for the elements of the highlighted general group Eval Un Eval This will flag the highlighted general group for allowing ignoring it during limit state 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 201 evaluation Do Undo Master This will make the highlighted general group s elements master elements so they do not show up when you display the coarse and fine mesh models at the same time When you view all modules the coarse elements used to create the fine mesh model will not be displayed overlapping the new fine mesh elements Create Patch This will create an evaluation patch using the elements of the highlighted general group Refine This will launch the Refine dialog and allow the user to create a fine mesh model of the elements in the highlighted general group Modify This will launch the Modify Properties dialog which allows the user to modify the highlighted general group s settings Modify Properties Composite Panel Top Layer Fiber Orientation Orientation Reference Direction Angle Degrees Plate Offset Offset Properties I Plate Pod Bar __ ie Rod lo Spring o Eje 2009 DRS Defense Solutions LLC Advanced Technology Center 202
66. opening the MAESTRO Strakes dialog box from the Model gt Elements gt Create Modify gt Strake menu or from the toolbar MAESTRO Strakes Name v General Plating Frames Girders Stiffeners Deletions Type Regular v Strake Connectivity EndPoint1 1 EndPoint2 2 Location Bottom v Create Modify Delete Close 2 Make sure the correct module is set to the current part and click the ID button to assign the strake a unique ID Note Frames can be defined as l beams by selecting Second Flange as the strake type This will use the selected T beam property for the frame and automatically add a second flange using the T beam flange properties See the Second Flange verification section for examples 3 Click in the EndPoint 1 box and then click the first end then the second end point defining the strake The two boxes should automatically update with the end point numbers Note you may click anywhere along the line of nodes making up the end point 4 Select the location of the strake Bottom Side Deck or Other This is important for MAESTRO to define the elements as wetted or not Bottom and Side will assign the shell elements as wetted 5 Click the Plating tab and select the plate property from the drop down menu A new property can be created by clicking the Property box 6 Click the Frames tab and select the frame property and Frame Web Orientation If there are no frames on this section there
67. or from the toolbar LoadCase v Name General End Moments Acceleration Mass Point Force Pressure Balance Constraint Corrosion Load Safety Factor Current Status From Other Menus Structure amp Loads Symmet Options on Masses amp Accelerations y F Include structure s mass Self Weight M Include gravity Floating Structure Ship etc Non Float Additional acceleration M Corrosion User defined CG Re define constraints Natural freq analysis Create Modify _Close Help 2 Click the LoadCase button to create a new load case 3 Give the load case a descriptive title 4 Check the desired options for the load case on the general tab and click Create 5 Click on each of the relevant tabs to define each aspect of the load case Note Fore more information on each tab option see the specific tab topics of this section 6 Repeat steps 2 5 to create additional load cases 2009 DRS Defense Solutions LLC Advanced Technology Center 208 MAESTRO 9 0 7 7 4 2 7 4 3 General Tab LoadCase v Name General End Moments Acceleration Mass Point Force Pressure Balance Corrosion Load Safety Factor 10 Current Status From Other Menus No S ti Options on Masses amp Accelerations pa aie y Include structure s mass Self Weight Has Point Load Mass Include gravity Has Immersion Floating Structure Ship etc Additional accele
68. point in the modeling space or entering the coordinates in the form of x y z at the command line For example to generate a cutting plane that is parallel to the Y axis but is ata 45 angle to both the X and Z axes specify a normal vector of 1 0 1 an origin of 0 0 0 and the visible side by clicking on a point on the model Removes all cutting planes from the model and restores the active viewport 2009 DRS Defense Solutions LLC Advanced Technology Center 122 MAESTRO 9 0 7 4 18 Security Devices The topics in this section provide details of how to updated the security device the Fast Lock utility and details regarding the use of network security devices 4 18 1 Updating Security Device It is very important you first have the two passwords available that were provided by ATC If you do not have these passwords you should contact ATC before continuing These passwords will allow the proper operation of MAESTRO and other optional modules If you are experiencing any problems with your security device please contact maestrosupport orca3d com Procedure for Updating the Security Device To update your security device perform the following steps 1 Locate passwords that have been provide by ATC or your MAESTRO dealer If you do not have passwords you will only be able to view the security device information Please contact maestrosupport orca3d com regarding passwords 2 Attach the security device
69. preliminary check for failure the Von Mises stress at the girder flange and the plate flange are calculated at each frame and at the mid length of the girder and if compressive are checked against the yield stress yo vm Ys Rorcr ocr where 2 2 2 O m zde F0 010 FT The bending stress is accounted for in either o or o A similar analysis is done to check failure against tension Frame Failure Modes MAESTRO s limit states for frames cover 5 different modes of failure The table below provides a summary of these failure modes 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 267 Frame Failure Modes FYCF Frame Yield Compression in Flange FYCP Frame Yield Compression in Plate FYTF Frame Yield Tension in Flange FYTP Frame Yield Tension in Plate FCPH Frame Collapse Plastic Hinge Frame Failure Modes Serviceability Serviceability limit states are defined when the deterioration or loss of other less vital functions have occurred Frame Yield Compression Tension Flange FYCF FYTF The Von Mises stress due to the combination of frame bending stress axial stress and shear stress at the root of the frame flange is calculated and compared to the yield stress RPFYCEFYTF own for FYCF for FYTF Oy where is given by Cu o R and where accounts for both the axial and the bending stress Frame Yield Co
70. pressure surface by specifying a point in structure coordinates through which the surface passes The Zero X Zero Y and Zero Z are the X Y and Z values in structure coordinates of a point through which the zero pressure surface passes The surface will automatically be normal to the total acceleration vector NOTE The words depth height and head always mean normal to the zero pressure surface which is also the direction of the total acceleration If the current load case includes any heel or trim or other rotation of the structure then the direction of the total acceleration is no longer parallel to the structure Y axis If the current load case includes any dynamic accelerations i e distinct from gravity then the zero pressure surface will rotate so as to remain normal to the total acceleration vector and the direction of the total acceleration will not be parallel to either the Y axis or the structure Y axis Additional Beam 2009 DRS Defense Solutions LLC Advanced Technology Center 222 MAESTRO 9 0 7 LoadCase Name General Mass PointForce Pressure Balance Plate LinPress Plate Surface Head Plate Surface Zero Additional Beam Edge Module Name Type Tag Pressure On Node 1 N mm 2 Pressure On Node 2 N mm 2 Width mm Modify DelRow Close Help The Additional Beam option allows the user to impose a pressure load to an additional beam Positive pressure acts in t
71. price paid This warranty is void if failure of the SOFTWARE has resulted from accident abuse or misapplication from any party other than Licensor EXCEPT AS EXPRESSLY STATED IN ARTICLE 4 LICENSOR DISCLAIMS ALL OTHER WARRANTIES WHETHER EXPRESS OR IMPLIED INCLUDING BUT NOT LIMITED TO THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS FOR A PARTICULAR PURPOSE NO AGENT DEALER OR DISTRIBUTOR IS AUTHORIZED TO MODIFY OR REVISE THIS WARRANTY LIMITATION OF LIABILITY IN NO EVENT SHALL LICENSOR BE LIABLE FOR ANY INDIRECT INCIDENTAL SPECIAL PUNITIVE OR CONSEQUENTIAL DAMAGES DAMAGES FOR LOSS OF BUSINESS PROFITS BUSINESS INTERRUPTION LOSS OF BUSINESS INFORMATION LOSS OF DATA OR LOSS OF GOODWILL ARISING OUT OF THE USE OF OR INABILITY TO USE THE SOFTWARE NOTWITHSTANDING ANYTHING HEREIN TO THE CONTRARY LICENSOR S TOTAL LIABILITY TO CUSTOMER AND ANY THIRD PARTIES SHALL NOT EXCEED THE AMOUNTS PAID BY CUSTOMER FOR THE LICENSED SOFTWARE HEREUNDER INDEMNITY In the event that a claim is brought against Customer alleging that the SOFTWARE or Documentation infringes a U S patent copyright or trade secret Licensor agrees to defend such claim and to indemnify and hold Customer harmless for any damages or costs awarded against Customer Customer shall give Licensor prompt written notice of any such claim shall allow Licensor to control the defense and settlement of such claim and shall reasonably cooperate with Licensor in the defense a
72. query icon y can be used to highlight a bare plate element and recover the stresses The drop down arrow next to the dynamic query icon can be used to select which stresses to display when highlighting an element Deformed Model Stress Adequacy List Export Output Contour MAESTRO will automatically calculate and report the 8 5 4 Stiffened Panel MAESTRO can recover stresses for a stiffened panel at the mid plane of the plate Top the neutral axis of the plate and stiffener combination Mid and the axial stress at the mid plane top s2 midbody m1 fr 25 49 strake 17 Quad Sec 12 Thickness 0 5 in FeTag 2562 Stresses Mid Ibf in 2 SigX 3 1309E 003 SigY 3 5466E 002 Tau 2 6448E 002 SigVM 3 0046E 003 Stresses Top Ibf in2 SigX 3 1750E 003 SigY 3 5831E 002 Tau 2 7390E 002 SigVM 3 0490E 003 Stresses Bottom Ibf in 2 SigX 3 0868E 003 SigY 3 5101E 002 Tau 2 5507E 002 SigVM 2 9602E 003 Corner Stress VM Ibf in2 C1 3 0104E 003 C2 3 1054E 003 C3 3 0053E 003 C4 2 9112E 003 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 245 of the stiffener flange Bottom Stiffener Flange The figure below presents these three locations tT op Mid plane of Plate Mid Stiffened Panel NA 2 a i Bottom Stiffener Flange Mid plane Stiffened Panel Stress Recovery Locations
73. recovery purposes Customer may not modify decompile disassemble reverse engineer reverse translate or prepare derivative works of the SOFTWARE in whole or in part at any time for any reason 3 COPYRIGHT The SOFTWARE is owned by Optimum Structural Design Inc hereinafter referred to as Licensor and is protected by U S copyright laws and international treaty provisions This License Agreement does not transfer any ownership in the SOFTWARE Documentation trademarks or other Licensor proprietary property rights 4 WARRANTY Licensor warrants that it is the owner of the SOFTWARE and Documentation and that the SOFTWARE and Documentation do not infringe any U S patent copyright or trade secret rights of any third party Licensor further warrants for a period of thirty 30 calendar days from the date of shipment that 1 the media on which a copy of the SOFTWARE is provided to Customer will be free from defects in material and workmanship under normal use and ii the SOFTWARE will perform substantially in accordance with the Documentation 5 CUSTOMER REMEDIES Licensor s entire liability for breach of warranty and the Customer s exclusive remedy for breach of warranty shall be at Licensor s option and 2009 DRS Defense Solutions LLC Advanced Technology Center 410 MAESTRO 9 0 7 expense either a repair or replacement of the SOFTWARE or media that does not meet the warranty or b return of the
74. remotely update the user s maintenance and support as well as update the user s optional modules Outside of updating the security device the Fast Lock utility is used to inform the user of the device s current configuration If you are experiencing any problems with your security device please contact technical support at maestrosupport orca3d com Interface The Fast Lock interface is very easy to use and understand nearly self explanatory a brief description follows File Menu Using the File menu the user can execute the Read Lock Print Print Setup and Exit commands Edit Menu The user can execute the Set Passwords command using this menu item The Set Passwords dialog seen below will then prompt the user to enter two passwords which is provided by ATC or your local MAESTRO dealer 2009 DRS Defense Solutions LLC Advanced Technology Center General 125 Set Passwords Password 1 Password 2 View Menu Using this menu the user can toggle on off the Toolbar an Status bar Help Menu This menu provides Fast Lock version information Current Lock Settings This area of the Fast Lock interface displays security device information This information includes Lock Type Number of Users License Number Expiration Date Support Due Date and Last Run Date Enabled Modules This area of the Fast Lock interface displays modules that are enabled 4 18 3 SafeNet Network Lock MA
75. s2 midbody m2 fr49 63 strake 14 Beam Sec 10 Property 18x4x5 16 L ST24 FeTag 1763 Stresses Ibf in 2 SigX 1 7916E 003 SigF Start 1 0904E 003 SigF End 3 0232E 003 SigF Mid 9 6640E 002 SigP Start 5 8298E 003 SigP End 6 6009E 001 SigP Mid 2 9479E 003 Tau Start 1 0229E 003 Tau End 1 0229E 003 Moments Ibfin Mom Start 4 3575E 004 Mom End 1 8621E 004 Shear Forces lbf SF Start 2 8271E 003 SF End 2 8271E 003 When querying a beam element all stresses including local axial stress and shear stress will be recovered as well as the bending moments and shear force at each end of the beam The stresses at the mid location of the plate connection and flange are calculated by linearly interpolating the appropriate stresses at the start and end locations of the beam Bare Plate MAESTRO will recover stress on a bare plate element at the top middle and bottom of the element The different stresses at each location of the element can be plotted by selecting the option from the Results menu The element local X local Y shear and Von Mises stresses can be plotted and recovered for each of the three locations on the plate element The figure below presents these three locations for a bare plate element 4 Top Mid Tito Bare Plate Stress Recovery Locations 2009 DRS Defense Solutions LLC Advanced Technology Center 244 MAESTRO 9 0 7 The dynamic
76. same as highlighting a part in the parts tree and right clicking and selecting Set View Part or selecting Tools gt Set View Part from the menu This icon allows the user to click a part in the model space to set it as the current part and current view It is the same as highlighting a part in the parts tree and right clicking and selecting Set Current amp View Part or selecting Tools gt Set Current amp View Part from the menu This icon allows the user to click a module in the model space and set it as a Transparent view It is the same as highlighting a part in the parts tree and right clicking and selecting Set Transparency On This icon allows the user to click a transparent view module and return it to the standard element type view It is the same as highlighting a part in the parts tree and right clicking and selecting Set Transparency Off F This icon toggles the view between solid and wireframe This icon toggles node visibility as on or off I This icon will toggle on and off stiffeners This is the same as opening the View Options dialog and checking Stiffeners This icon will toggle on and off the water plane This is the same as opening the View Options dialog and checking Water Plane Note to turn on the CG and CF markers you must still open the View Options dialog 4 This icon toggles the background color between black and white 2009 DRS Defense Solutions LLC Advanced Technology Cent
77. should be a property with no frames defined A new property can be created by clicking the Property box 7 Click the Girders tab and if applicable click the Enable Girder box and select the girder property and Angle in degrees If there is no girder to be included in the current strake make sure the Enable Girder box is unchecked 8 Click the Stiffeners tab and if applicable choose the stiffener layout desired If no layouts are defined or to create a new layout click the Layout button or the Stiffener Layout icon from the toolbar See the Stiffener Layouts section for more information 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 159 Stiffener Layout Identification Name x ID nd Property Property v ID v MAESTRO Settings Number of Internal Stiffeners 0 Edge 1 Stiffener C Breadth Between Stiffeners Edge 2 Stiffener Create Modify Delete Close 9 Click the ID button to assign a unique ID and enter a descriptive name for the stiffener layout Note the first stiffener layout should be a null property This gives the option to define an unstiffened strake or quad 10 Select the stiffener property from the drop down menu If the beam element property desired is not already defined a new one can be created by clicking the Property button 11 The stiffener layout can be defined by number of internal stiffeners or by defining the breadth betw
78. task into a few distinct subtasks in order to maintain a good overview and control of the design Most large structures can be reduced to several levels of component structures for which the design and analysis is relatively independent Such a structure can best be modeled by subdividing it into a hierarchy of parts down to the module level and then constructing each module using a three dimensional mesh of nodes and appropriate groupings of finite elements As shown below in Figure 1 the MAESTRO structural modeling is organized into four levels members elements strakes modules and substructures 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 129 LAN MODULE ELEMENTS SUBSTRUCTURE A collection of Modules SHIP Figure 1 Hierarchy of Structural Modeling MAESTRO Elements The basic unit of structural modeling is a principal member such as a transverse frame red beam stiffened panel dark blue girder yellow beam rod brown line etc as shown below in Figure 2 In order to have an efficient interaction between the finite element analysis and the optimization the finite elements in MAESTRO are in most cases the same as the principal members The elements are therefore relatively large e g a complete panel from one deck to another and from one frame to the next or a corresponding segment of a transverse frame or longitudinal girder The fin
79. that select box Once an element is added to the group right clicking on the element will bring up a menu 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 189 allowing the user to flip normal side or add all elements with the same property material stiffener layout or type This will apply to all elements in the current view part 7 The Normal of the element can also be flipped by double clicking in the Flip Normal column to change between Yes and No Once the Flip Normal is changed to Yes or No it will remain the same as new elements are added to the definition 8 The mass of the plate group can be defined here and will be used if the plate group is added to a load case as a mass 9 Select a color from the drop down menu to give the plate group a unique color 10 Click the Create button The new plate group will appear under the group tab of the parts tree under the plate folder as the name given in the Groups dialog box Module Group A module group is a group of module s used to scale up the structural weight of a model This group is used to define a non structural mass whose spatial distribution closely approximates the surrounding structure The mass is distributed among the structural nodes in the same proportion as the structural mass and can represent items such as furniture paneling auxiliary machinery or any additional structural weight This can also be used
80. the Name box 4 Click in the white space and then click the nodes to be added to the group Checking the All visible nodes in the section will add all the nodes in the section of the next clicked endpoint node Note this must be unchecked to add an additional node to the group 5 Check the Centerline Group if the node group spans the centerline of a half model This will automatically combine the mirrored group into one single group if the model is mirrored 6 Define the mass weight of the node group Each node will receive an equal portion of the total mass weight Note if the nodal group is made up of only centerline nodes the mass weight should be assigned the full value regardless of whether is is a half model 7 Select a color from the drop down menu to give the section group a unique color 8 Click the Create button The new node group will appear under the group tab of the parts tree under the Node folder as the name given in the Groups dialog box 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 193 Bay Group This group option is intended for large solid masses that are supported at several nodes and whose center of mass is at an appreciable distance from these nodes Common examples are bays of containers main engines and un modeled portions of structure such as masts Bays and the sets of masses within them are selected individually by using the groups dialog In ad
81. the mechanical properties of the panel element are changed However the location is relevant when creating a fine mesh model from the coarse mesh model At this point an actual beam element will be created representing the properties of the stiffener at the defined location e When two end points coincide at the reference or opposite end is there a difference between using a strake triangle or an additional triangle element No in the case of a strake element with coinciding reference of opposite end points the triangular element is degenerated to a simple triangle e Do I need to define the second strake for girders when running the sparse solver No The second strake is used to identify the girder s effective breadth for the hybrid beam formulation in the scalable solver e How is the additional stiffness treated when a quad or strake has a stiffener layout The axial and bending stiffness of the stiffener s defined on that plate element are smeared into the panel s property If an edge stiffener is defined MAESTRO adds the 2009 DRS Defense Solutions LLC Advanced Technology Center 384 MAESTRO 9 0 7 12 3 axial and bending stiffness of the whole stiffener to the panel on which the stiffener is defined e Can I sort the plate and beam properties in the strake definition dialog or the additional elements dialogs Yes element properties can be sorted in the properties dialog by name thickness
82. the tick by increasing decreasing the point load scale on the right side of the View Options dialog box 5 Once the orientation is verified click the Direction checkbox once more to change it from Fiber to Stress 6 Click OK 7 The displayed Stress X is now in the given direction Stresses can be recovered in each layer of a composite shell element The following steps will detail the procedure to recover stresses from each of the layers 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 285 1 Solve the model 2 Select one of the stress options from the Results gt Stress menu 3 Click the Layers icon to turn on layers 4 Click the dynamic query icon gt 5 Highlight an element and right click to bring up the menu to choose which stress direction to display as well as to choose the composite layer at the bottom of the menu biimodi L 02 Lateral Pressure 1 46E 003 1 74E 003 2 87E 003 3 15E 003 3 43E 003 v Stress Local Y F Stress Local XY E ee 3 71E 003 Stress Von Mises 2 s Stress Shear X ae 3 99E 003 Stress Shear Y Stress Ratio Layer Stress Ratio DeBond acl 4 27E 003 Strain Local X Strain Local Y 4 55E 003 Strain Local XY Max 4 83E 003 Min Top 1 Bottom 5 11E 003 5 39E 003 5 67E 003 6 95E 003 6 Once a stress option is chosen from the dynamic query fly out menu highlighting an e
83. to define all of the properties except for the node locations After creating this prototype rod select the Rod option from the drop down menu The user can now single click on the first node in the model that is to become the element node 1 in the new rod and then double click on the second node Repeat this process for as many rod elements as you wish but remember these new rods are based on the properties of the 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 177 prototype rod After completing the Quick Creation sequence there are two important things to remember The first is to toggle off the quick creation icon and second the Quick Creation process does not update the ID numbers in the dialog box Therefore if you are going to continue using the dialog box you must close the Finite Element Dialog Box and the reopen it Spring Creation The user must create a prototype spring element in the usual manner for the other elements This will serve to define all of the properties except for the node locations After creating this prototype spring select the Spring option from the drop down menu The user can now single click on the first node in the model that is to become the element node 1 in the new spring and then double click on the second node Repeat this process for as many spring elements as you wish but remember these new springs are based on the propert
84. to the Main Menu and clicking on Edit MAESTRO Out If necessary enlarge the Output pane by dragging its upper boundary upward Right click and select Find Enter objective function and click on Find Next This will take you to page 19 of the output which has a table of scantlings at the start of cycle 4 a restart job maintains the original cycle numbering The scantlings are all the same as at the end of the third cycle of the first job except that there are now no girders Therefore the weight cost and objective function are all less than before For example the objective function is now 0 753 compared to 0 782 before or about 3 less As can be seen in Figure 1 this 3 savings is reflected in both the cost and the weight because they were given equal importance Most of this savings is due to the elimination of the girders In reality the savings in cost would be still greater because of the elimination of the connections between frames and girders which is not considered in the simple cost function being used here The results of design cycle 5 are given on pages 35 37 There are now only 10 active constraints page 35 because there are only 10 design variables As shown on page 37 the objective function is now 0 748 only slightly less than the starting value and so we conclude that the optimization has essentially converged The Final Evaluation results are given on pages 38 54 Page 55 is the histogram from the evaluation c
85. to the USB port NOTE PARALLEL PRINTER PORT SECURITY DEVICES ARE NO LONGER SUPPORTED 3 Click MAESTRO Fast Lock from the Start gt Program Files gt MAESTRO menu The dialog below will appear 2009 DRS Defense Solutions LLC Advanced Technology Center General 123 Hardware Lock Utility Maestro FastLock EL OX Current Lock Settings Lock Type Network NetSentinelC Number Of Users Lock Defaut License Number EE Expiration Date None available Support Due Date Thu Jui 92 2009 Last Run Date Mon May 042009 Enabled Modules Base MAESTRO Module RS 1 Bay Only Static Solver Module ANSYS Translator Module Eigenvalue Module ALPS ULSAP Standalone Optimization Module Fine Mesh Module Nastran Translator Module ULSAP Evaluation Module ALPS HULL Progressive Ultimate Strength 4 Choose Read Lock from the File menu Atthis point the Fast Lock utility will report your current options 5 Choose Set Passwords from the Edit menu The dialog below will appear 2009 DRS Defense Solutions LLC Advanced Technology Center 124 MAESTRO 9 0 7 4 18 2 Set Passwords Password 1 Password 2 6 Enter both Password 1 and Password 2 7 Click OK The lock is now updated Fast Lock Security Device Utility Fast Lock is a utility that allows the user to update and maintain their MAESTRO security device This utility provides the capability to
86. trans vert coords weight floating point END ENTITY Entity 4 Hull Parameter Data HYDRO Note Indenting is used for clarity only not used in actual file IDF 3 01 or greater SENTITY HYDRO VESSEL NAME Identifier for this vessel DATA SOURCE program that wrote the file DATE mm dd yy TIME hh mm ss SUNITS 2009 DRS Defense Solutions LLC Advanced Technology Center 398 MAESTRO 9 0 7 This line must be either SI or User Defined If User Defined then the following line s must be specified of user units meter of user units square meter of user units cubic meter of user units kg COORDINATE SYSTEM coordinates of a point one unit forward starboard down coordinate gnomon e g for FAST SHIP 1 1 1 COMMENTS This is a comment about the ship about to be described Can be any of 79 character lines GEOMETRY n number of parts or surfaces part 1 part n where each part is PART part name entry 1 entry n END ENTITY Each entry is an ITTC computer symbol from the Interim Standard Transfer Set ISTS a subset of the ITTC list of Standard Symbols and Terminology entered in the following form 2009 DRS Defense Solutions LLC Advanced Technology Center Appendices 399 computer symbol value For example the ITTC computer symbol for length of waterline is LWL For a ship with a waterline length of 451 5 the data would be enter
87. using the dynamic query function 8 5 2 Beam In addition to the specific beam stress options the Mid X Normal and Mid Von Mises are the only stress options that will graphically display the beam element s axial stress Stresses can be recovered from the start and end locations of a beam element at the flange and connection between the beam and plate The Figure below shows the location of the recovered stresses 2009 DRS Defense Solutions LLC Advanced Technology Center 242 MAESTRO 9 0 7 2 Plate end Flange end Plate start es Flange start Beam Element Stress Recovery Locations Flange Start Flange End Plate Start Plate End Flange Max Tension Flange Max Compression The beam stress menu from Results gt Stress gt Beam gt allows the user to select the location of the recovered stress to plot graphically The Flange Max Tension and Flange Max Compression options will plot the higher of the compressive or tensile stresses at the beam flange from either the start or end location The beam stress results menu is only used to select which stress value to plot for each beam element The dynamic query icon can be used to highlight a beam element and recover the stresses Double clicking the element will echo the results to the Output tab 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 243 8 5 3 WO top
88. value Q by a certain factor called the safety factor g Expressed mathematically the safety requirement is yQ lt Q If we define a strength ratio r 19 Q then the safety requirement becomes R lt 1 Each of these requirements constitutes a constraint on the design In MAESTRO each constraint is expressed in the form g R gt 0 Safety against structural failure is measured by a parameter called the Adequacy parameter denoted by g R which is defined as The advantage of using an adequacy parameter of the strength ratio is that g always lies within the normalized limits of 1 and 1 whereas R ranges from 0 to infinity Specifically g R 1 as R gt 0 either as a result of very small load or very large limit value and at other extreme g R gt 1 as R gt either as a result of very large load or very small limit value Since all of the constraints in MAESTRO are of the above form it is sufficient in explaining each of the failure types to simply explain what is Q and Q for that failure type For convenience of reference in post processing each of the adequacy parameters for both MAESTRO and ALPS ULSAP is identified by an acronym usually consisting of four letters First it should be states that there are two broad categories of limit states i e 2009 DRS Defense Solutions LLC Advanced Technology Center 256 MAESTRO 9 0 7 8 9 1 adequacy parameters the ultimate or collapse li
89. vody Delltem Close 3 Right click on the group in the parts tree and select Refine 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 291 Model Refinement FineMesh Module Name general group 001 Join Tolerance 1e 005 m User Defined Module Origin optional m fe Defaut UserDefined Analysis Type Top Down Embedded ALPS HULL C Nastran Map Load Control oO ciate M Map Loads Mesh Controls Minimum length along non stiffened edge O default m Minimum of segments between stiffeners 4 Conver beam frame girder web to 1 Quad Convert beam frame girder s flange to Beam z Cancel 4 Select Embedded for Analysis Type and use the default values for the rest of the input and click OK You should now be to the same point as FineMeshStep2Embed mdl In an embedded analysis the coarse mesh elements from the general group are now replaced by the fine mesh elements 2009 DRS Defense Solutions LLC Advanced Technology Center 292 MAESTRO 9 0 7 The fine mesh and coarse mesh models will now solve simultaneously in an embedded analysis Again RSplines are used to transmit the displacements of the coarse mesh nodes to the fine mesh nodes along the RSpline element ALPS HULL Analysis Due to the complexity of this subject please see the ALPS HULL section Nastran Map Analysis The Nastran Map option will c
90. window which is found at the bottom of the MAESTRO GUI In conjunction with the View Net Force command the user can use the Dynamic Query tool which can be initiated via the LM icon to query the distribution graph To use this functionality the user must select the View Net Force command toggle the Dynamic Query icon and move the mouse cursor over a particular portion of the graph This will produce a text box with graph data The user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph entity of interest 2009 DRS Defense Solutions LLC Advanced Technology Center General 75 Net Force lbf 2 21E 003 TT pyr prt T TTT SSE Ee is F 3 16E 003 TI lii t 4 12E 003 pes i 5 08E 003 M 6 04E 003 7 00E 003 7 96E 003 8 92E 003 9 88E 003 View Longitudinal gt The View Longitudinal menu has several options to display the longitudinal properties of the modeled structure A detailed description of each of these options is below Bending Moment Torsional Moment Element Effectiveness All Sections Properties Iz lyy Cross Sectional Area Neutral Axis Shear Center Warping Constant Torsonal Rigidity Shear Force 2009 DRS Defense Solutions LLC Advanced Technology Center 76 MAESTRO 9 0 7 Bending Moment Torsional Moment Element Effectiveness All Sections Properties Izz lyy Cr
91. 003 8 54E 003 9 ATE 003 1 04E 004 1 13E 004 1 23E 004 1 32E 004 141E 004 1 51E 004 View Buoyancy The View Buoyancy command under the the Hull menu is used to display the FE model s buoyancy distribution for the selected load case as shown below Further MAESTRO echoes this distribution to the Output window which is found at the bottom of the MAESTRO GUI In conjunction with the View Buoyancy command the user can use the Dynamic Query tool which can be initiated via the me icon to query the distribution graph To use this functionality the user must select the View Buoyancy command toggle the Dynamic Query icon and move the mouse cursor over a particular portion of the graph This will produce a text box with graph data The user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph entity of interest 2009 DRS Defense Solutions LLC Advanced Technology Center 74 MAESTRO 9 0 7 Buoyancy lbf 1 49E 004 1 40E 004 1 30E 004 1 21E 004 1 12E 004 1 02E 004 7 44E 003 er re I Hill Iiii TE 6 51E 003 58E 003 4 65E 003 3 72E 003 2 79E 003 1 86E 003 9 30E 002 0 00E 000 View Net Force The View Net Force command under the the Hull menu is used to display the FE model s net force distribution for the selected load case as shown below MAESTRO also echoes this distribution to the Output
92. 09 DRS Defense Solutions LLC Advanced Technology Center 350 MAESTRO 9 0 7 RPSPBL Panel Serviceability Plate Bending Longitudinal 2 18 Updating the DAT file by Copying and Pasting from the Restart File The restart files are text files similar to the input data file jobname DAT When a module has been sufficiently optimized the designer should transfer its final optimum scantlings from the restart file into the appropriate place in the job data file This transfer is accomplished by copying and pasting using a text editor such as NotePad For example with the NotePad editor the procedure would be as follows for Example 2 1 Within the File option Open the restart file ex2_no_girder S01 2 Highlight the lines containing the final optimum scantlings do not include the last line containing the objective function cost and weight 3 Within the Edit option Copy these lines to the Paste buffer 4 Go back to the File option and Open the original dataset file EX2 DAT 5 Go to the beginning of Data Group IX of the module corresponding to this restart file in this example there is only one module 6 Highlight the lines containing the old scantlings 7 Within the Edit option Paste the lines from the restart file into the data file The result is that data groups IX X and XI of the job data file now contain the final optimum scantl
93. 2 2 2 On Sala PO Oo y cO vm Oy Recmy p where Own Von Mises stress y combined safety factor for collapse Panel Collapse Stiffener Buckling PCSB In previous versions the input data for MAESTRO evaluation component such as panel pressure stresses plate thickness and stiffener scantlings are the average quantities over the corresponding patch Since Evaluating PCSB Panel Collapse Stiffener Buckling does not require to use the width of the grillage or patch it is more appropriate to evaluate these failure modes at the element level rather than the patch level which is now the behavior for this limit state For panels that have longitudinal stiffeners of open cross section this limit state refers to panel collapse due to flexural torsional buckling of the stiffeners The theory is given in 2009 DRS Defense Solutions LLC Advanced Technology Center 262 MAESTRO 9 0 7 Section 15 5 of Ref 1 If the stiffeners are of closed cross section this limit state refers to buckling of the side wall of the stiffener For transversely stiffened panels the stiffeners are at right angles to the principal compressive stress and so they can do little to prevent or delay plate buckling However if they buckle before the plating then overall panel buckling follows immediately This is a very undesirable mode of collapse since it occurs rapidly and without warning Therefore the PCSB limi
94. 4 703 0 168011 173 353 0 0345482 162 801 162 647 17C 18 9 168 OK 6 09895e 006 2 80144e 006 6 80121e 006 7 8984e 009 570 162 316 226 288 162 1 11399e 015 171 099 6 60503e 014 218 79 200 901 16 a9 10 168 OK 7 85837e 006 4 33535e 006 6 80121e 006 4 01499e 009 668 842 372 906 341 842 1 58273e 015 188 478 5 24646e 015 194 27 183 522 18 20 10 192 OK 8 23971e 006 4 9153e 006 7 64531e 006 4 74314e 009 691 969 392 093 345 782 9 17897e 016 184 497 4 22546e 014 186 226 223 503 18 al 11 192 OK 8 84784e 006 5 32129e 006 7 64531e 006 4 78391e 009 713 15 395 931 365 626 6 23444e 015 189 595 3 06075e 014 183 794 218 405 18 FE 11 216 OK 9 29461e 006 6 01364e 006 8 57483e 006 5 49961e 009 736 89 415 213 370 083 3 87873e 015 185 49 6 72182e 015 176 193 258 51 18 E 12 216 OK 1 2545e 007 6 25389e 006 1 05784e 007 2 21879e 010 784 447 431 931 404 575 5 39791e 016 229 068 4 69204e 014 189 5 214 932 22v s a _ nn RS a E LIN Command Output Grid LI 2i Izz The View Longitudinal gt Izz command under the the Hull menu is used to display the FE model s inertia properties about the z axis for each section as shown below In conjunction with the View Longitudinal Izz command the user can use the Dynamic Query which can be initiated via the tay icon to query the distribution graph To use this functionality the user must select the View Izz command toggle the Dynamic Query icon and move the mouse cursor over a particular portion of the graph This will
95. 49E 013 6 56E 013 7 64E 013 Bending Moment The View Horizontal gt Bending Moment option is used to display the FE Model s horizontal bending moment distribution Further MAESTRO echoes this distribution to the Output window which is found at the bottom of the MAESTRO GUI In conjunction with the View Horizontal Bending Moment command the user can use the Dynamic Query which can be initiated via the LM icon to query the distribution graph To use this functionality the user must select the View Horizontal Bending Moment command toggle the Dynamic Query icon and move the mouse cursor over a particular portion of the graph This will produce a text box with graph data Further the user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph entity of interest 2009 DRS Defense Solutions LLC Advanced Technology Center 92 MAESTRO 9 0 7 1 10E 009 9 31E 010 ETEEN l TTT 4 11E 010 2 38E 010 6 45E 011 1 09E 010 2 82E 010 4 55E 010 6 29E 010 8 02E 010 9 75E 010 View Transverse gt Shear Force Bending Moment Torsional Moment Shear Force The View Transverse gt Shear Force option is used to display the FE Model s transverse shear force distribution Further MAESTRO echoes this distribution to the Output window which is found at the bottom of the MAESTRO GUI In conjunction with the View Tran
96. 50 Freq 11 691 Hz Mode 7 is converged Number of iterations 3 Freq 11 7666 Hz Mode 8 is converged Number of iterations 130 Freg 13 5731 Hz Mode 9 is converged Number of iterations 128 Freg 13 6828 Hz Mode 10 is converged Number of iterations 3 Freg 13 8431 Hz Model Participation Factor Model Effective Mass Mode Frequency Eff M xx ACU Eff M yy ACU Eff M zz ACU 1 1 9155 3601 849 0 73 416959 601 84 33 0 488 0 00 2 4 4225 1519 570 1 04 16 492 84 34 0 280 0 00 3 5 4626 441294 245 90 29 1230 083 84 59 17 364 0 00 4 6 6501 40236 968 98 43 55 418 84 60 0 648 0 00 5 10 8164 2308 512 98 90 41593 216 93 01 10 606 0 01 6 11 6910 102 532 98 92 8367 377 94 70 0 220 0 01 7 11 7666 287 932 98 98 5660 535 95 85 0 264 0 01 8 13 5731 111 973 99 00 146 785 95 88 59 656 0 02 9 13 6828 19 150 99 00 37 712 95 88 5 303 0 02 10 13 8431 204 034 99 04 344 739 95 95 5 329 0 02 TOTAL 489687 474412 100 159 ACU is the accumulated modal participation factor Modal effective mass and participation factor are relative measurement to the total vibration For example if the ACU is 99 in the first five modes it implies the first five modes are dominant modes and the rest of the modes can often be ignored Modal effective mass and participation factors are often used in constraint vibration such as Dynamic Design Analysis Method DDAM To view the different mode shapes select the natural frequency analysis load case from the load case drop
97. 66E 000 VM4 1 9321E 000 Double clicking on a node or element will output the results to the output window at the bottom of the screen 8 All element stress results nodal forces or reaction forces can be output to the grid tab by selecting from the Results gt List gt menu This spreadsheet can be easily copy and pasted into another program if desired If a Failure Mode Evaluation method was selected for the analysis the results can be graphically displayed from the Results gt Adequacy menu The adequacy parameters menu will be different depending on whether MAESTRO or ULSAP evaluation is chosen MAESTRO ULSAP 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 249 All Load Cases Minimum Value Plate PCSF Collapse Stiffener Flexure PCCB Collapse Combined Buckling PCMY Collapse Membrane Yield PCSB Collapse Stiffener Buckling PYTF Yield Tension in Flange PYTP Yield Tension in Plate PYCF Yield Compression in Flange PYCP Yield Compression in Plate PSPBT Serviceabiity Plate Bending Tran PSPBL Serviceabiity Plate Bending Long PFLB Failure Local Buckling Mimimum Value Beam GCT Tripping GCCF Collapse Compression in Flange GCCP Collapse Compression in Plate G F YCF Yield Compression in Flange G F YCP Yield Compression in Plate G F YTF Yield Tension in Flange G F YTP Yield Tension in
98. 6E 006 SSR D m nnm 742E 006 pm 6 18E 006 4 95E 006 3 71E 006 2 47E 006 1 24E 006 0 00E 000 Cross Sectional Area The View Longitudinal gt Cross Sectional Area command under the the Hull menu is used to display the FE model s cross sectional area properties as shown below In conjunction with the View Longitudinal Cross Sectional Area command the user can use the Dynamic Query which can be initiated via the ty icon to query the distribution graph To use this functionality the user must select the View Cross Sectional Area command toggle the Dynamic Query icon and move the mouse cursor over a particular portion of the graph This will produce a text box with graph data Further the user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph entity of interest 2009 DRS Defense Solutions LLC Advanced Technology Center General 85 Area in2 1 19E 003 1 11E 003 1 04E 003 9 65E 002 8 91E 002 7 43E 002 6 69E 002 5 95E 002 21E 002 447E 002 sm 7 3 73E 002 M 2 99E 002 2 25E 002 1 51E 002 7 69E 001 2 92E 000 Neutral Axis The View Longitudinal gt Neutral Axis command under the the Hull menu is used to display the FE model s neutral center as shown below In conjunction with the View Longitudinal Neutral Axis command the user can use
99. 849 292 414 3 44497e 015 top s4 ss mi 16177 8 1897 32 120 871 1 32663e 014 top s3 stern mS fr76 78 22654 4 1829 38 111 383 6 75135e 015 top s3 stern m4 fr73 76 38067 9 1653 57 87 7209 2 73467e 014 top s3 stern m2 fr65 70 19399 6 1758 45 103 198 1 14446e 014 top s3 stern m3 fr70 73 93144 3 1391 71 77 5474 7 83947e 015 top s2 midbody m2 fr49 63 18939 8 1570 96 82 3971 1 87559e 014 top s3 stern ml fr63 65 260905 915 796 72 7569 7 69649e 015 top s2 midbody ml fr 25 49 28355 6 542 067 77 3852 1 21798e 014 top s1 bow m6 fr21 25 4112 36 94 0377 97 2812 3 44927e 015 top s1 bow m2 fr3 5 38284 6 423 341 80 4336 0 726928 top s1 bow mS fr15 21 25028 6 297 575 84 4411 7 88505e 015 top s1 bow m4 fr10 15 20181 2 177 04 92 1842 6 35634e 015 top s1 bow m3 fr5 10 3655 53 40 7391 115 769 8 43551e 016 top s1 bow ml frl 3 708493 924 837 116 622 0 0392808 gt Total Module Weight Full Ship Exclude Tank Weight 708493 Total Self Weight Included in Total Module Weight 708493 924 837 116 622 0 0392808 gt Total Force due to Weight Full Ship 7084941bE EEE Summary of Module Self Weight WEIGHT 1b XCG in YCG in ZCG in Module Name 119587 372 849 292 414 3 44497e 015 top s4 ss ml 16177 8 1897 32 120 871 1 32663e 014 top s3 stern mS fr76 78 22654 4 1829 38 111 383 6 75135e 015 top s3 stern m4 fr73 76 38067 9 1653 57 87 7209 2 73467e 014 top s3 stern m2 fr65 70 19399 6 1758 45 103 198 1 14446e 014 top s3 ster
100. By application of the finite element method quite accurate ultimate strength solutions have been obtained in several specific cases by a number of investigators However a weak feature of the conventional finite element method is that it requires enormous modeling effort and computing time for large sized structures Therefore most efforts in the development of new calculation methods have focused on reducing modeling and computing times The obvious way to reduce modeling effort and computing time is to reduce the number of degrees of freedom Modeling the object structure with very large sized structural units is perhaps the best way to do that Properly formulated structural units in such an approach can then be used to efficiently model the actual nonlinear behavior of large structural units Ueda and Rashed 1974 1984 who suggested this idea called it the idealized structural unit method ISUM For applying ISUM various structural units making up the object structure should be developed in advance Until now several ISUM units have been developed and based on these units a family of the computer program ALPS has been written by Paik 1995b ALPS 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 271 is an acronym for the nonlinear Analysis of Large Plated Structures The ALPS HULL module calculates efficiently the progressive collapse behavior of ship hulls The benefit
101. C Advanced Technology Center 142 MAESTRO 9 0 7 Set Current Part Set View Part Rename Copy Mirror Delete Add Mirror Set Visibility On Set Visibility Off Visibility List Set Transparency On Set Transparency Off Show Weight Set Current Part This will set the highlighted module or substructure as the current part Set View Part This will set the highlighted module or substructure as the current view If a substructure is selected all the modules in that substructure will be visible To view the entire model highlight and right click top and select Set View Part Set Current amp View Part This will set the highlighted module or substructure as the current part and the current view Rename This will allow the highlighted module or substructure to be renamed within the parts tree Copy This will create a copy of the highlighted module or substructure Mirror This will launch the mirror dialog and allow the user to Mirror or Add Mirror for the highlighted part Delete This will delete the highlighted module or substructure If a substructure is deleted all of its 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 143 5 6 modules will be deleted as well Add Mirror This will launch the mirror dialog and allow the user to Mirror or Add Mirror for the highlighted part Set Visibility On This will toggle the visib
102. DRS Defense Solutions LLC Advanced Technology Center 366 MAESTRO 9 0 7 11 1 6 Scordelis Lo Roof The sixth test is the Scordelis Lo roof problem The structure is loaded by its own weight From the given conditions in Figure 1 the specific weight is 360 unit volume This problem has the combination of in plane and out of plane loads This is the only slightly curved shell problem in the test set It is required to correctly distribute the body force to four grid nodes The results of this test are listed in Table 1 I de aw 4 Figure 1 Scordelis Lo Roof Radius 25 0 Length 50 0 t 0 25 E 4 32e98 v 0 Loading 90 0 per unit area in Z direction BCs Load esh Size Theoretical MAESTRO MSC Nastran Max M 4x4 Self Weight scod nas scod f06 Simple Support at r 360 Both Unit Circular Volume 8x8 0 3086 ae Eee Table 1 Scordelis Lo Roof Results As shown in Figure 2 MAESTRO s typical coarse mesh modeling 4 elements per side for a 2009 DRS Defense Solutions LLC Advanced Technology Center Verification and Validation 367 total of 16 elements has an order of accuracy 3 6 that ABAQUS only achieves with 16 elements per side for a total of 256 elements 3 4 Deflection 03086 03190 03225 mie THEORETICAL MAESTRO 03881 ABAQUS 4 8 16 No of elements per side Figure 2 Comparison of MAESTRO and ABAQUS Results
103. ELT for the web heights and flange breadths of the frames This item is similar to Items 6 and 7 except that it applies to the frames The default value is 20 0 for mm 0 020 for m and 0 5 for inches 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 Verification and Validation Verification and Validation 359 11 Verification and Validation The topics in this section provide test results for MAESTRO element verification studies and compare these results to theoretical and other FEA software results All data files referenced in the following sections can be found in the MAESTRO installation directory under MAESTRO Models amp Samples Verification Models 11 1 Quad The following sections provide various verification tests for MAESTRO s quad element 11 1 1 Patch Test For the patch tests there are five files in all Three of them are set up for the constant in plane strains corresponding to tensions in X Y direction and shear in X Y plane The other three files are for constant bending curvature corresponding to pure bending in X Y direction and pure twist Table 2 gives the boundary conditions loads and the theoretical strains and stresses for the patch elements for the five tests The MAESTRO recovered stress and displacements are presented along with the results from MSC Nastran for Windows V3 0 for comparison The patch test model geometry is presented in Figure 1 The loca
104. ESTRO relies on a hardware lock to provide license security MAESTRO can be run in a network environment in which MAESTRO is installed and used on many client workstations with security handled by a single hardware lock installed on a central server machine Interaction between MAESTRO and the hardware lock is handled by a security server program that must be running on the server machine where the lock is installed The system that handles network security is known as Sentinel Protection Server and is developed by SafeNet Inc The installation of all security components including the Sentinel Protection Server is bundled into the installation of MAESTRO Please refer to the SafeNet ReadMe paf file which can be found in the following directory C Program Files MAESTRO System Sentinel 2009 DRS Defense Solutions LLC Advanced Technology Center 126 MAESTRO 9 0 7 4 19 NOTE MAESTRO has a mechanism to release a network license 10 minutes after a crash occurs Alternatively a user with Administrator computer privileges can Restart the Sentinel Protection Server manually via the MS Windows Services dialog See the About Sentinel License Monitor section of the SafeNet ReadMe paf for further troubleshooting tips Installation Directory and Sample Files By default MAESTRO is installed in a MAESTRO directory located in the user s Program Files Upon a successful installation of MAESTRO the following three directories w
105. Less a Initial Design BFF 9 min BGF 9 min TGF BGF 25 TFF BFF 25 BSF 16 TS N a f a TFW HFW 50 TPL 0 48 TGW HGW 50 HSW 36 TSW HGW 1 1 HFW b Scantlings and Constraints at End of Cycle 3 BFF 9 min TFF BFF 5 BSF 16 TSF HN TFW HFW 50 TPL 0 5 EME RS HSW 36 TSW c Scantlings and Constraints of Final Design 2009 DRS Defense Solutions LLC Advanced Technology Center Figure 2 Scantlings and Governing Constraints at 3 Stages Tutorials 355 10 2 4 Appendix A Appendix A Format for Specifying the Discretization Data excerpt from the Data Preparation Manual 9 1 3 DISCRETIZE Data Group This optional group allows the designer to specify allowable thicknesses and size increments for the final values of the design variables If this group is included then in the last design cycle the program will round off each of the hitherto continuous values of the design variables to one of the allowable discrete values The evaluation cycle is then performed on these discrete values Each rounding off may be either up or down depending on the current structural adequacy of the affected structure and on roundoff fractions specified by the designer FIRST LINE ITEM 1 DISCRETIZE or NODISCRETIZE keyword the first four letters are sufficient NODISCRETIZE indicates that strake design variables will not be rounded to the specifi
106. MAESTRO Manual MAESTRO Structural Modeling Software Copyright 2009 Optimum Structural Design Inc MAESTRO This software is protected by U S and Intemational copyright laws MAESTRO 9 0 7 Table of Contents Part Part Il 1 Part Ill 1 Part IV AN OO OO BR WN mn 4 1 ON OO OU BR WN Foreword 0 Welcome to MAESTRO 9 0 7 7 Latest Updates 9 KATEA oTa 9 02 its sel tiescct E tcc nn en ten lend Gans sess nd dt is 9 Introduction 14 About MAESTRO 552355 aeea te inerte cee eal AN AAA AE Sec nu AAE A A ANATESEA EAE ec ENRERE rente uses 14 DESIGM SYSUOM Mea E T T A E cod ET 14 Finite Element Modeling ssir ieyra n ahaaa eaaa eaa aeaaeae anaana daeh iaeaea a EA aa ddat a aoa a ten aaa i radaras eadeni ainada 17 Checking Your MOdel ai ar eee raa raa a aara arae eaaa aa de aAa ere aee Pae doe a Eea teens aaaea reaa aa tunes 2 18 Analyzing Yo r Model a a r Tr te aaa a ae ete aE aa me men ne oaaae Daia 19 POSt PrOCESSING siecscciscnceciantuaiecrneoasstacbandacnpdisesnsnaevccaduasoaseabaaveaaiadterbedssaveuesuceasoasouncendvadsudsedecsesududdbavbabdsercareaupaiecei 20 Getting Help tn RP en TE 20 How to buy MAESTRO eeaeee eannan ea ne ne aes 22 eiae Started A cestesetdenedecatesstuzcantedesscp esdaeseedets 22 General 25 Workspace Layouts 25 File Men r 55 25 ae E cae aac eae a eae en Sa ce E 29 TOONS M nt 2 5 000288 teens cose aaraa raaa eaat eaaa A e Aa Aaaa aa a
107. Orientation checkbox c Define a desired global orientation for the group d Click OK 2009 DRS Defense Solutions LLC Advanced Technology Center 284 MAESTRO 9 0 7 8 12 View Options EndPoints Labels amp Entities Visibility Off Additional Nodes Off Strake Labels Strake Plates Strake Frames Strake Girders Stiffeners Compounds Quads Triangles Beams Rods Springs RSplines Brackets Tools amp View Style Viewports Single C Split Vertical Off lv On M On Jv On Off Jv On Jv On Jv On lv On lv On Jv On M On F Split Horizontal C Four Views 3 Launch the View Options dialog zi Video Driver Options Hardware Z buffer Advanced F KA Master Elements w On Plate Offset Water Plane Scale Water Plane Width Constraints Point Loads Point Moments Markers Spring RSpline Off Off J des de Jea lja M Solid Wireframe Shrink Elements M Construction Geometry M Cutting Planes World Axes Recovering Composite Layer Stresses Plot Legend Fonts sans serif v Color white x Size 12 Width 2 Blocks 16 a X a X a X Pre Post processing Deformation Scale Range F Apply Defined Range Corner Stress ALPS HULL Off Off Cancel 4 Click the Direction checkbox once Off will change to Fiber next to the checkbox A small tick should be shown at each element centroid You can scale
108. Plate FCPH Collapse Plastic Hinge Minimum Value All Negative Positive All Load Cases Minimum Value Plate PCPM Plate induced failure at Midspan PCCB Overall Grilage Collapse PCPE Plate induced failure at Panel Edges PCSB Stiffener induced failure tripping PCWB Panel Collapse Web Buckling PYM Yield in Mid Plane PYF Yield in Flange PYP Yield in Plate Mimimum Value Beam BCT Tripping BYC Gross Yielding BCWB Web Buckling BCC Collapse Beam Column FCPH Collapse Plastic Hinge Minimum Value Al Negative Positive 2009 DRS Defense Solutions LLC Advanced Technology Center 250 MAESTRO 9 0 7 8 7 Selecting one of the parameters will display the patches colored by their adequacy parameter value MAESTRO can automatically display each elements smallest adequacy parameter by selecting Minimum Value Plate Minimum Value Beam or Minimum Value All You can also choose to display only the Positive or only the negative adequacy parameter results The dynamic query icon ti v with Adequacy checked from the drop down can be used to highlight an element and recover the adequacy parameters Double clicking the element will echo the results to the Output tab Viewing Stress Ranges Toolbar Menu View gt Options The following tutorials shows the basic functionality for viewing stress ranges for a given load c
109. Quads RSplines Brackets El Connectivity Node 1 Node2 Node3 Property amp Stiffeners Property f ID J test i Wetted Reverse Normal Rotate Local X Create Modify Delete Close 2 Make sure the appropriate module is set as the current part and click the ID button to assign a unique ID to the element 3 Click in the Node 1 box and click the three nodes that make up the triangle element in the model 2009 DRS Defense Solutions LLC Advanced Technology Center 162 MAESTRO 9 0 7 4 Select the plate property from the drop down menu If the property is not defined click the Property button to create a new plate element property 5 Check the Wetted box if the element is part of the bottom or side shell 6 Click Create This procedure can be repeated to create additional triangle elements Toolbar Menu Model gt Elements gt Create Modify gt Beam This tutorial shows the procedure for creating an individual beam element 1 Begin by opening the Finite Element Beam dialog using the Model gt Elements gt Create Modify gt Beam menu the toolbar or clicking the Beam tab in the Finite Elements dialog box Finite Elements Springs Rods Beams Triangles Quads RSplines Brackets ID v Connectivity Node 1 Node 2 Property Property Null Beam Prop ID 00001 v Web Orientation By Associated Element Web Orientation Transv
110. Robert L Harder A Proposed Standard Set of Problems to Test Finite Element Accuracy Finite Elements in Analysis and Design 1 pp 3 20 1985 16 Cowper G The Shear Coefficient in Timoshenko s Beam Theory Journal of Applied 2009 DRS Defense Solutions LLC Advanced Technology Center Appendices 389 13 2 13 3 Mechanics Vol 33 1966 pp 335 340 17 O F Hughes and Ming Ma Elastic Tripping Analysis of Asymmetric Stiffeners Computers and Structures Vol 60 No 3 1996 pp 369 389 18 O F Hughes and Ming Ma Inelastic Stiffener Buckling and Panel Collapse Computers and Structures Vol 61 No 1 1997 pp 107 117 19 O F Hughes Two First Principles Structural Designs of a Fast Ferry All Aluminum and All Composite Fourth International Conference on Fast Sea Transportation Volume pages 91 98 July 1998 Sydney Australia B Data Prep Manual For the legacy Data Preparation Manual click here C IDF Specification INTERNATIONAL MARINE SOFTWARE ASSOCIATES INTERFACE DEFINITION FILE IDF REVISION 3 03 5 May 1997 The IMSA IDF is intended to be a neutral file format for exchange of hull description data between marine programs without the generality or complexity of standards such as IGES and DXF and without the specific traits of a particular program s native format The file is designed to be easily human readable Compactness is sometimes sacrificed for this
111. TE SYSTEM coordinates of a point one unit forward starboard down coordinate gnomon e g for FAST SHIP 1 1 1 COMMENTS comments comments GEOMETRY data format specific to geometry type from here down 2009 DRS Defense Solutions LLC Advanced Technology Center Appendices 391 END ENTITY Current Entity Types Entity Type Description SECTIONS Sectional Data Stations Buttocks Wls 3d curves MESH Surface Mesh data NURBS NURBS Surface data HYDRO Hull Parameter data AREA Sectional Area Data PROPSECTS Propeller Geometry Data General Comments This standard contains only one interface file This file can contain one or more entities where each entity is a specific data type e g hull sectional data NURBS surface data etc This avoids having many different files and allows new entities to be added as necessary It also means that one file can contain different types of data for a single ship sectional data surface data etc thus avoiding many files describing the same ship The file will be a simple ASCII file so that it will be transportable across different hardware platforms as well as being easily human readable While this does not result in the most compact format it does result in a format that is easy to produce read add to and modify Data for each line item are to be separated by commas Comments may be added on any line following an exclamation mark End of line sequenc
112. TRO 9 0 7 LoadCase Name General Mass PointForce Pressure Balance Plate LinPress Plate Surface Head Plate Surface Zero Additional Beam Edge Full Strake Compound v AddPlate Group Module Name Type D Head mm Density kg mm 3 Modify Del Row Close Help The Surface Head option is intended for hydrostatic pressure for which the value is proportional to the depth below the free surface of a fluid or other zero pressure plane In the Surface Head option the pressure is always an actual pressure For strake panels the pressure varies linearly across the strake width in proportion to the local depth below the zero pressure surface and in the lengthwise direction it is constant over each panel and is calculated separately for each panel based on the depth of that panel below the zero pressure surface For additional non strake panels and triangles the pressure is calculated at each corner of the element and then multiplied by either one fourth or one third of the element area NOTE The words depth height and head always mean normal to the zero pressure surface which is also the direction of the total acceleration If the current load case includes any heel or trim or other rotation of the structure then the direction of the total acceleration is no longer parallel to the structure Y axis If the current load case includes any dynamic accelerations i e distinct from gravity then the zero
113. The SOFTWARE will run for fifteen 15 calendar days after installation Upon the expiration of this 15 day period the Customer shall either i purchase an ongoing license by paying the stipulated License Fee which shall be subject to the terms and conditions of this License Agreement or 11 promptly remove or uninstall the SOFTWARE and return it 2009 DRS Defense Solutions LLC Advanced Technology Center 412 MAESTRO 9 0 7 14 15 16 to Licensor or at the Licensor s option destroy the SOFTWARE and certify to such destruction EXPORT COMPLIANCE Customer agrees to comply with all applicable export laws and regulations arising or related to its performance under this License Agreement The Customer shall not export re export disclose transfer furnish or otherwise provide the SOFTWARE to any foreign person as defined by the International Traffic in Arms Regulations as amended 22 C F R Parts 120 130 including those working for the Customer whether within the U S or abroad without obtaining in advance a appropriate U S government export authorization and b written approval from the Licensor NOTICE TO U S GOVERNMENT END USERS The SOFTWARE and Documentation are commercial items as that term is defined at 48 C F R Part 2 101 consisting of Commercial Computer Software and Computer Software Documentation as such terms are defined in 48 C F R Part 252 227 7014 a 1 and 48 C F R
114. The Sections Bay and Cylinder Length can be defined here The sections per bay defines the number of strake sections per structural bay This allows for the transverse frames to be placed every second section or third section or any other regular spacing The Reference End and Opposite End Frame options defines whether a transverse frame will be located at either end of the module s strakes 14 Click Modify Additional modules can be created in the same manner for the current substructure or other created substructures Parts Tree The parts tree pane displays the hierarchy of substructures and modules in the model in a folder format directory The parts tree can be manipulated just as a directory tree can but the user must remember that modules must be contained in substructures The tree can be shown or hidden using the parts tree icon 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling Workspace s1 bow m1 fr1 3 m2 13 5 m3 fr5 10 m4 fr10 15 m5 fr15 21 m6 fr21 25 s2 midbody B m1 fr 25 49 m2 fr49 63 s3 stern m1 fr63 65 m2 fr65 70 m3 fr70 73 m4 fr73 76 m5 fr76 78 s4ss mi The number and organization of the parts may be adjusted either through the Parts 141 command on the main menu or directly in the parts tree Clicking the right mouse button launches a popup menu offering the user several options 2009 DRS Defense Solutions LL
115. Top The Plate X Normal Plate Y Normal Plate XY Shear and Plate Von Mises stresses can be recovered at the mid plane of the plate for a stiffened panel from the Results gt Stress gt Top gt menu Plate X Normal Plate Y Normal Plate XY Shear Plate Von Mises The dynamic query icon can be used to highlight a stiffened panel and recover the stresses in the plate Double clicking the element will echo the results to the Output tab Mid The X Normal Y Normal and Von Mises stresses are recovered at the neutral axis of the stiffener and plate structure The shear stress reported for Mid is the Plate Shear stress from the mid plane of the plate The dynamic query icon 7 can be used to highlight a stiffened panel and recover the stresses in the plate Double clicking the element will echo the results to the Output tab Bottom Stiffener Flange The only stress recovered for a stiffened panel at the bottom location is the axial stress at the mid plane of the stiffener flange This can be graphically displayed by selecting either Results gt Stress gt Bottom gt Stiffener Axial Flange or selecting the appropriate stress direction Normal X or Normal Y corresponding to the orientation of the stiffener If bottom Normal Y stress is chosen from the Results menu any stiffened panels with longitudinal stiffeners will be grayed out because the axial stress of the stiffeners is orientated in the X direction 2009 DRS Defense So
116. We also need to make a new restart file Recall that in order to avoid overwriting the output file ex2_no_girder OUT which would disturb the page numbering we made a new Modeler file for cycle 6 called ex2_cycle6 mdl Normally this would not be necessary it was only done because of the Tutorial But since we did make a new Modeler file we must also make a new restart file that has the same name We cannot do this by File Save As because the Modeler can only read mdl files We will do it by renaming the current restart file 2009 DRS Defense Solutions LLC Advanced Technology Center Tutorials 349 In the Main Menu click on File Open In the Open dialog box go to the bottom click the down arrow on Files of type and select All Files Select the file called ex2_no_girder sO1 right click and select Rename Rename the file to ex2_cycle6 s01 Close the Open dialog box Now we are ready to perform the sixth cycle during which the scantlings will be discretized In the upper toolbar click on the Execute icon Select Yes to generate a new DAT file After the job has completed enlarge the Output pane by dragging its upper border Bring up the output file Edit MAESTRO Out The final scantlings all of which are now standard sizes are given in the table on page 28 of the output Notice that the number of stiffeners is now an integer The new design is illustrated in Figure 2 As shown in Figure 1 the objective
117. a particular portion of the graph This will produce a text box with graph data Further the user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph entity of interest 241E 013 2 11E 013 1 81E 013 1 50E 013 1 20E 013 8 95E 014 5 91E 014 2 88E 014 1 60E 015 3 19E 014 6 23E 014 9 26E 014 1 23E 013 1 53E 013 Shear Force The View Horizontal gt Shear Force option is used to display the FE Model s horizontal shear force distribution Further MAESTRO echoes this distribution to the Output window which is found at the bottom of the MAESTRO GUI In conjunction with the View Horizontal Shear Force command the user can use the Dynamic Query which can be initiated via the thd icon to query the distribution graph To use this functionality the user must select the View Horizontal Shear Force command toggle the Dynamic Query icon and move the mouse cursor over a particular portion of the graph This will produce a text box with graph data Further the user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph 2009 DRS Defense Solutions LLC Advanced Technology Center General 91 entity of interest 6 30E 013 2 01E 013 VIP EYE EEEIEE 0 1 1 ra Et Er EI SEE 1 I LE VE LI 1 LEL fl 9 42E 014 1 30E 014 1 20E 013 2 27E 013 3 35E 013 4 42E 013 6
118. ab in the Finite Elements dialog box Finite Elements Spring Rod Beam Triangle Quad RSpline Bracket El Connectivity Node 1 Node 2 Property Property Create Modify Delete Close 2009 DRS Defense Solutions LLC Advanced Technology Center 164 MAESTRO 9 0 7 2 Make sure the appropriate module is set as the current part and click the ID button to assign a unique ID to the element 3 Click in the Node 1 box and click the two nodes that make up the rod element in the model 4 Select the rod property from the drop down menu If the property is not defined click the Property button to create a new rod element property 5 Click Create This procedure can be repeated to create additional rod elements RE Menu Model gt Elements gt Create Modify gt Spring This tutorial shows the procedure for creating a spring element 1 Begin by opening the Finite Element Spring dialog using the Model gt Elements gt Create Modify gt Spring menu the toolbar or clicking the Spring tab in the Finite Elements dialog box Finite Elements Spring Rod Beam Triangle Quad RSpline Bracket E Connectivity Node 1 Node 2 Property Property v ID v Create Modify Delete Close 2 Make sure the appropriate module is set as the current part and click the ID button to assign a unique ID to the element 3 Click in the Node 1 box and cl
119. ace The pink face of the element will receive the positive pressure As seen below a typical tank will have the pressure side on the inside of the tank This is very important when defining tanks 2009 DRS Defense Solutions LLC Advanced Technology Center 44 MAESTRO 9 0 7 In conjunction with the Volume Plate Pressure Side view the user can use the Dynamic Query tool which can be initiated via the tay icon to Flip Pressure Side define the volume group as a Centerline Group and Remove an element associated with the group When using this functionality the user can also choose to switch between the Element Pressure Side view or the Tank Group Pressure Side view This aids in the building of tanks To use this functionality the user must first change to the Volume Plate Pressure Side view toggle the Dynamic Query icon move the mouse cursor over a particular element right click the mouse and finally select the menu item Constraints This option displays the model in wireframe view showing the nodes that are constrained and in which direction 2009 DRS Defense Solutions LLC Advanced Technology Center General 45 Edges Free Edges 3 Edges 4 or More Free Edges This option will check the model for free edges and can create a group of potential free edge errors if desired It is easiest to see the free edges in red when the model is in wireframe view 2009
120. acy will be dealt with by some other means outside of the optimization process In the Limit States subpage double clicking to the right of a limit state acronym will generate a nullify tag 2 6 Defining Constraint Sets That Are Strake Specific Thus far the Constraint Sets that have been defined are intended to be used for all strakes Therefore when we come to the third page of the Dialog Box they will be placed in the Standard Group But it often happens that there are some strakes for which we want to define some special different data such as a special constraint To do this we create a new Constraint Set in which we define that new data Then when we come to the third page of the Dialog Box we will place that Constraint Set in a General Group which is associated with those strakes 2009 DRS Defense Solutions LLC Advanced Technology Center 334 MAESTRO 9 0 7 Group Optimization Settings Overall Defaults Constraints Structure ID 00003 v Name Constraint Set00003 v Create Delete Modify Plate Girder Frame Stiffener Other Limit State Variable Operator Number of Stif min max Breadth Between Stif in gt Web Thickness in min max Web Height in min max Flange Thickness in min max Flange Height in min max HSW TSW lt BSF TSF BSF HSW min max TSW TPL lt Acronym Close For example the above figure show
121. alog box will notify the user of this otherwise the elements exceeding the aspect ratio will be identified with a color corresponding to the aspect ratio as defined in the legend on the right of the screen Elements that do not exceed the aspect ratio will be gray The Output tab at the bottom of the screen will also list the elements exceeding the aspect ratio and their corresponding aspect ratio 4 Select View gt Element Type from the menu to return to the element type view Menu Tools gt Integrity Check gt Internal Angle 1 This integrity check can be performed from the Tools gt Integrity Check gt Internal Angle menu option 2 A dialog box opens allowing the user to set the maximum allowable internal angle the default value is 150 0 degrees 3 If there are no elements exceeding this internal angle a dialog box will notify the user of this otherwise the elements exceeding the internal angle will be identified with a color corresponding to the internal angle as defined in the legend on the right of the screen Elements that do not exceed the internal angle will be gray The Output tab at the bottom of the screen will also list the elements exceeding the internal angle and their corresponding internal angle 4 Select View gt Element Type from the menu to return to the element type view Menu Tools gt Integrity Check gt Warped Quad 1 This integrity check can be performed from the Tools gt Integrity
122. ample The above explanation is given because in this example for the sake of simplicity the boundary conditions for the relevant portion of the structure are assumed to be already known which is not the usual situation Normally the analysis portion of the design process would deal with all of the modules simultaneously such that in the analysis and in the subsequent module by module evaluation and optimization all of the modules have the correct boundary conditions automatically and at all times But for this simple introductory example we restrict ourselves to just one module The boundary loads and external pressures are 1 a lateral pressure on each strake of 12 psi 2 an alternating hog sag vertical bending moment for which the characteristic value expected maximum lifetime value with an acceptably small probability of exceedance is 1 95x108 lb in To be consistent with these loads and to preserve their symmetry the shear force at the ends is taken as zero The program s echo print of the loads is given on pages 8 13 of the output which you obtain by going to the Main Menu and clicking File gt Analysis Evaluation gt Legacy Version of MAESTRO gt View Output File 1 5 Partial Safety Factors The partial safety factors for this example are obtained from the American Petroleum Institute Bulletin 2V Design of Plane Structures The loads described above correspond to the extreme service condition for which the fac
123. an be used to query an element to recover the pressure and double clicked to echo the information to the output tab Surface Head This option will display the pressure of the panel elements for which a surface head is defined for the currently selected load case The dynamic query icon can be used to query an element to recover the pressure and double clicked to echo the information to the output tab Surface Zero This option will display the pressure of the panel elements for which a surface zero is defined for the currently selected load case The dynamic query icon can be used to query an element to recover the pressure and double clicked to echo the information to the output tab Additional Beam This option will display the pressure of the additional beam elements for which a pressure is imposed for the currently selected load case The dynamic query icon canbe used to query a beam element to recover the pressure and double clicked to echo the information to the output tab Edge This option will highlight the edge of elements where an additional stress is applied Similar to the free edges view the edges where a stress is applied will show up in red All This option will display the net pressure on the elements for the currently selected load case The dynamic query icon can be used to query an element to recover the pressure and double clicked to echo the information to the output tab 2009 DRS Defense
124. an now double click on the construction marker in the model Repeat this process for as many additional nodes as you wish After completing the Quick Creation sequence there are two important things to remember The first is to toggle off the quick creation icon and second the Quick Creation process does not update the ID numbers in the dialog box Therefore if you are going to continue using the dialog box you must close the Reference Points Dialog Box and the reopen it Strake Creation The user must first create a prototype strake in the usual manner for the other strakes This will serve to define all of the future strake properties except for their endpoint connectivity After creating this prototype select the Strake option from the drop down menu The user can now single click on the first endpoint of the strake and then double click the second endpoint of the strake Repeat this process for as many strakes as you wish but remember these new strakes are based on the properties of the prototype strake After completing the Quick Creation sequence there are two important things to remember The first is to toggle off the quick creation icon and second the Quick Creation process does not update the ID numbers in the dialog box Therefore if you are going to continue using the dialog box you must close the Strake Dialog Box and the reopen it Quad Creation The user must create a prototype quad in the usual manner for the other
125. anced Technology Center 232 MAESTRO 9 0 7 Import MAESTRO dat File Lookin Desktop f 3 My Documents My Computer My Network Places G My Recent Documents a 5 My Documents a fi Fiename My Network Files of type MAESTRO Data Files dat Cancel MAESTRO mdi Two existing MAESTRO models can be combined into one using the Import gt MAESTRO mdl menu option This functionality can be useful when two different users are creating different parts of a model and want to combine them In order to combine the two files open one of the files and choose File gt Import gt MAESTRO mdl from the menu 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 233 Add Model Lookin MAESTRO OC Ey Help Models and Samples system My Recent Documents My Documents File name My Network Files of type MAESTRO Modeler Files mdl Cancel Choose the MAESTRO file to be imported and click Open If there are duplicates between the two models separate dialogs will open and give the option to use existing properties and materials or create new ones Material Data Creation Material name default already exists Do you wish to create a new material named default No will cause all elements which reference this name to reference the existing data ee ee Nastran
126. aora aE P Oaia ta aea deat opevaessaates 33 View Memb aE E E ETT TT T 37 Model Me NUn ae chet cadens cd tate sabe aaa a edie aeaa eaaa aa a aa eaae ee nn eee sn Aaaa Se a aea ea tatin ste 58 Groups Menu EE E P E E E E T A na 63 ETEA ae a E A A a E soveeedzenute odes ieeetasacncesecdact tes 65 LIR Ea e Dee E E E anes ceed A A A S 70 Results M nu 52 5 588885 88e Anne Sa E a a Oa ae M aasia ea adka gaie 94 Help Menu ariiraa EE EAER E AE TE 97 TOOIDAFTS 2225 Rececdezsccctzessccteadtendasseee cawesee ox eaeeeccates ons aar RAe aie Aaa Aaa en eua aE nee den Tenue nets dont esse aeta ss 98 Standard VieWS spainean ne nn aden nn ns at nn nas en 104 Aetna o AA EAn e aa ck seek toca ced See dectendecetes Defense benne E nent ons c age nes beteluseduwdenestsuunseuecsete 111 Using the Mouse amp Shortcut KeyS ss siennes 112 View ODON S svcccceccseceesass aneen taara ssn ebonne mue re sscecme sans sun ne sa sa med tmn din Se AAA e area OE aata anaco ss soute 116 Auto Save and Recover Model 119 Cutting PIANC 5555 rs et die rare ententes Teen ets e ne lt rer eaaa 120 Security Devices Rs ne Bae ee en At deren eee 122 Updating Security Device arrr e rrea ra a arra E r Ea a e Ee T AE aa a deusvestersuesedeedeeouseusevcsasavetesteaseesesese 122 Fast Lock S curity Device Utility nn e enr ra A a a eaae aY 124 2009 DRS Defense Solutions LLC Advanced Technology Center Contents 3 19 Part V MN OO OO BR WN
127. are multiple sub keywords present The presence of a third token will allow MAESTRO to start the batch process If a third token is not present MAESTRO will simple launch the GUI with the selected model open An example batch file maestro bat is found in the Models and Samples Advanced Batch Processing directory of the MAESTRO installation directory An example would be first_token second_token third_token cd system modeler90 exe ex1_ulsap mdl run Keywords The following keywords are available to support batch processing and accessing results for a given fetag The keywords have been categorized into Processing and Post processing Processing The batch processing is initiated by the presence of a third token as described above The example above uses run as the third token which would initiate the batch process with the default Analysis and Evaluation setup parameters If the model consists of fine mesh analysis models the Sparse solver will be used as the solver method The default Analysis and Evaluation setup parameters and behaviors are e Equation Solver Method Sparse e Beams Attached to Plating Eccentric Beam e Stresses amp Reaction Forces Calculate Stress amp Calculate Reaction Forces 2009 DRS Defense Solutions LLC Advanced Technology Center Advanced 313 e Failure Mode Evaluation None e A log file containing all of the results will be generated Keyword hybrid Used to cha
128. area A is the area of only the beam itself flange and web The bending stiffness parameter is B El L in which the neutral axis position and the moment of inertia are calculated for the combined section formed by the beam plus a plate flange of effective breadth b The element nodes are located at the neutral axis of the combined section as shown in figure 8 14 Thus in the hybrid element the plate s contribution to the beam bending stiffness is accounted for in the calculation of and the expression for the beam stiffness matrix remains unchanged 1 lt A shaded orea area for axial stiffness i HYBRID BEAM ELEMENTS Figure 8 15 Use of the hybrid beam element 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 231 Failure Mode Evaluation For detailed information on the two types of failure mode evaluations available see the Failure Mode Evaluation section 8 2 Importing an Analysis Model MAESTRO has the ability to import several types of analysis models MAESTRO dat MAESTRO mdl and Nastran DXF GHS IDF MAESTRO dat MAESTRO mdi Nastran Ship Motion smn MAESTRO dat The Import gt MAESTRO dat allows user to import a legacy data input file and converts it to an equivalent mdl file For a complete description of the dat file see the Legacy Data Preparation Manual 2009 DRS Defense Solutions LLC Adv
129. arse mesh and fine mesh model together select View gt All Modules from the menu Contour Plot Fave oo Menu Results gt Contour MAESTRO has the functionality to produce a contoured deformation or stress plot by toggling on the icon or selecting Results gt Contour from the menu A check mark will appear in the menu next to this option when contour view is toggled on 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 295 Total Dis in 6 94E 001 6 50E 001 6 07E 001 5 64E 001 4 3 90E 001 347E 001 3 03E 001 2 60E 001 2 17E 001 1 73E 001 1 30E 001 8 67E 002 4 33E 002 0 00E 000 Deformation Contour Plot MAESTRO s contour plot is either a nodal contour which averages all values at the nodes or an average elemental centroidal stress depending on whether the Corner Stress option is checked in the View Options dialog Nodal contouring produces a smooth contour plot but the results will not be accurate at material boundaries or property breaks As a result the nodal contour plot should not be used across material boundaries or changes in properties such as plate thickness as this will produce inaccurate results Elemental contouring however is useful for models with multiple materials and plate elements with varying thicknesses 8 15 Transparency View View gt Set Visibility gt Visibility On View gt Set Visibility g
130. art options This can also be done by clicking the Set Current amp View Part icon a Integrity Check gt This option opens the integrity check options menu allowing the user to choose one of the functions to check the model Aspect Ratio Element Connectivity Internal Angle Overlapped Elements Warped Quad Compute gt The Compute menu has two options to calculate parameters of the modeled structure A detailed description of each of these options is below 2009 DRS Defense Solutions LLC Advanced Technology Center General 35 Center of Flotation amp CG Gyradius Center of Flotation amp CG This option will calculate and output the center of flotation and center of gravity to the output tab as well as graphically display the waterplane and CG and CF locations Flotation Center in xCF 1009 9 yCF 107 827 zCF 0 Centroid in xCG 924 759 yCG 116 619 zCG 0 Radii of Gyration CG in xGyrCG 164 038 yGyrCG 530 4 zGyrCG 522 853 Total Mass 1 09e 006 lbf Mass Matrix Inertias CG lbm in 2 Ixx 2 93303e 010 Ixy 1 94846e 010 Ixz 6 40073e 009 Iyy 3 06643e 011 Iyz 2 72446e 008 Izz 2 97979e 011 Radii of Gyration CF in xGyrCF 164 274 yGyrCF 537 189 zGyrCF 529 812 Mass Matrix Inertias CF lbm in 2 Ixx 2 94145e 010 Ixy 2 03005e 010 Ixz 3 92949e 009 Iyy 3 14544e 011 lyz 7 94355e 008 Izz 3 05964e 011 4 gt Command Output Grid LJ Gyradius This option will compute t
131. ase The user will first define and apply a range and then optionally hide any elements outside of this defined range 1 After the results have been loaded click on the Result menu to open the drop down menu Deformed Model Stress gt Adequacy List Export Output gt Contour 2 Click on Stress and select which stress to display 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 251 rests Ia Deformed Model 5 1 v 48 w Mid X Normal Adequacy gt Mid Y Normal Plate i Mid XY Shear Plate List gt i E Mid Von Mises Export Output gt Top d Bottom Beam Contour Directional Define Direction Show Direction A detailed description of each type of stress that can be recovered can be found in the Stress Results sections 3 Click on the View Options icon amp or select View gt Options from the menu 4 From the View Options dialog see below click the Apply Defined Range checkbox This will enable the Min and Max Range fields for the user to define the stress range of interest 2009 DRS Defense Solutions LLC Advanced Technology Center 252 MAESTRO 9 0 7 8 8 View Options Labels amp Entities Visibility Plot Legend EndPaints Off Master Elements v On Fonts sans serif Additional Nodes Off Plate Offset Off Color white Strake Labels 7 Of Water Plane off F
132. aster and secondary nodes of a fine mesh model The nodes that correspond to global nodes will be shown in pink and the fine mesh secondary nodes will be shown in yellow In other words this option will display the master pink and secondary yellow nodes for the R Spline elements that translate the displacements between the global and fine mesh models 2009 DRS Defense Solutions LLC Advanced Technology Center General 53 All Modules This option is used to view the global coarse mesh model with the fine mesh model s shown on top of the coarse mesh elements 2009 DRS Defense Solutions LLC Advanced Technology Center 54 MAESTRO 9 0 7 Ma LS ASS Ly 17 HS ih dy cS D QS ar RSS eS 27 27 wa ii 7 Ny Lf l DA Uh Lit ih y Lee A SOR Y 7 OX oes SSA PN 2 AY RS fp AT A Fi PIX Element X Axis amp Global X Global Y Global Z Global X This option will color the elements corresponding to the angle that the element s local x axis makes with the global x axis 2009 DRS Defense Solutions LLC Advanced Technology Center General 55 oe 5 06E 001 me 4 50E 001 O 5 ail m 2 81E 001 3 94E 001 2 25E 001 1 69E 001 1 12E 001 5 62E 000 0 00E 000 Global Y This option will color the elements corresponding to the angle that the element s local x axis makes with the global y
133. atch 1 Create a general group It is suggested the group to be named as Eval abcdefg1 2 Expand the group tree and select the created group 3 Right click the mouse and select Create Patch from the menu How do you query a patch 2009 DRS Defense Solutions LLC Advanced Technology Center 280 MAESTRO 9 0 7 1 From the Dynamic Query icon MT select patch 2 Use the mouse to highlight the desired structure How do you evaluate a patch interactively 1 From the main menu Select Model gt Evaluation Patch gt Create Evaluate or click the patch icon Bl to open the Limit State Creation Evaluation dialog box 2 Select a patch from the ID drop down box and click compute M Limit State Creation Evaluation Identification Method ID Text Output ULSAP Name Parameter Set x C MAESTRO Input Data Evaluation Type E Auto C Userdefine fe Panel Beam Column Name Value X Value Y Length mm Width mm Thickness mm Material Initial Shape Init Maximum Deflection mm Compressive Residual Stress N mm 2 Init Maximum Deflection mm Compressive Residual Stress N mm 2 Breadth Heat Affected Zone for Aluminium mm Stress Lower N mm 2 Stress Upper N mm 2 Stress Shear N mm 2 Pressure N mm 2 Create Modify Compute Close How do you view the properties of a patch 1 O
134. ates based see Hughes of every member and every load case The solver performs three integrated tasks e finite element analysis to obtain the actual stresses and deflections throughout the model for all load cases 2009 DRS Defense Solutions LLC Advanced Technology Center Introduction 15 e calculation of the failure stresses for all relevant modes of failure for every member and every load case e a complete evaluation of the structural adequacy of every member under each load case and thereby obtaining a rigorous assessment of the current design of the structure which includes identifying the most critical failure mode and load case for each member Finemesh Analysis The MAESTRO Fine Mesh module allows the user to create refined 3 D FEA models of any portion of the MAESTRO model quickly The user creates a group made up of elements from the area of interest then refines the group based on two options The first option being the Top down mode In this mode Fine Mesh Analysis applies displacements from the global analysis to the fine mesh model for boundary conditions In the Embedded mode the second option Fine Mesh Analysis replaces the coarse mesh portion of the model with the fine mesh Eigenvalue Solver Natural Frequency MAESTRO can compute the natural frequency of the ship in either air or water When the analysis is done in water the added mass of the water is automatically applied to the wette
135. axis 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 56 OOE 001 44E 001 6 19E 001 9 00E 00 7 87E 00 6 75E 00 6 19E 00 62E 00 1E 001 5 06E 001 y M V q W N 3 94E 001 3 37E 001 2 81E 001 2 25E 001 ES 777 DIR 1 69E 001 1 12E 001 5 62E 000 0 00E 000 This option will color the elements corresponding to the angle that the element s local x axis makes with the global z axis Global Z 2009 DRS Defense Solutions LLC Advanced Technology Center General 57 ical Z 9 00E 001 8 44E 001 87 01 7 31E 001 6 75E 001 6 19E 001 JE F A 1 1 M l 5 62E 001 ES Ja D i 1 5 06E 001 iF f ih Mi jA 7 EN 4 50E 001 IKE i Ay 3 94E 001 mr 3 37E 001 2 81E 001 2 25E 001 1 69E 001 1 12E 001 5 62E 000 0 00E 000 Top Layer Fiber Direction This option will show the panel s top layer for composite panels primary fiber direction This orientation can be changed via the Results gt Stress gt Define Direction dialog For a composite model it is important to understand that redefining the primary fiber direction should be done prior to solving the model The Models and Samples folder in the installation directory contains three sample composite models demonstrating this functionality T
136. betdesaoadsaveareabiecsanseaseeuaderoatecdaavedocsataeseacevoubaresbiasadsdesoan 355 Verification and Validation 359 2009 DRS Defense Solutions LLC Advanced Technology Center Contents 5 N Oo Oo BB N Part XII OO N a Part XIII 1 Part XIV Quad en A E E E E A E ETEA Pateh TES aat aea ra aaaea ru e es ares a oan Aa aaia adepane au er td sias iniaa Cantilever Beamin aaa aeaea aaa aaa daara ana ae edarien aeaaea C rved Beam ea eraan a derenan aeara ea iaraa A ei e a ao odnada ea Twisted Bedin a r r a aa ai dan Eiaa a i adada Sadee bi dadanan aan Rectangular Plate Under Lateral Load ssssssssunnennnnnnnnnnnnnnnnnnnnn Scordelis Lo ROOf nt Hemispherical Shell FROGS RE ER Rens Added Mass Bracket serando nes ne en ae Rte atch tee ae co Hydrostatic Balance S cond Flange 7 0088 nr nent eines RBES sine nn nee nes dresse reee reste tes Eain Frequently Asked Questions General QUESTIONS Pre Processing ns Post ProcessiNg 7 terne Licensing and Security Device Appendices A References nes B Data Prep Manual C IDF Specifications License amp Copyright Index 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 Welcome to MAESTRO 9 0 7 Welcome to MAESTRO 9 0 7 7 1 Welcome to MAESTRO 9 0 7 MAESTRO Structural Modeling Software Copyright 2009 Optimum Structural D
137. bpage whereas the Other subpage allows the definition of more complicated constraints on the design variables and some special constraints relating to the entire module Examples are given in the following figure Group Optimization Settings Overall Defaults Constraints Structure 1D Jf00002 Name Constraint Set 00002 v Create Delete Modify Plate Girder Frame Stiffener Other Limit State Add Remove RHS gt 1 15000 300000 The first constraint illustrates the more general form that is available This constraint requires that the total height of the cutout in the frame web for the stiffener penetration must not exceed 70 of the frame web height The height of the cutout is taken as the stiffener web height plus a semicircle 1 inch in radius The constraint is then In the data input the two design variables must be on the left hand side and the constant term on the right hand side Hence the MAESTRO form of the constraint is 0 7 HFW 1 0 HSW gt 1 0 2009 DRS Defense Solutions LLC Advanced Technology Center Tutorials 331 Group Optimization Settings Overall Defaults Constraints Structure un foo002 Name Constraint Set 00002 Plate Girder Frame Stiffener Other Limit State Add Remove Constraint 1 The above figure shows the Other subpage after the frame web cutout constraint has been generated by th
138. btained in each design cycle Each restart file has the name jobname sMN where MN is the cumulative module sequence number numbering all the modules sequentially among all the substructures The new and consistent restart file that we just created is ex2_no_girder sO1 Once a consistent restart file has been created the optimization can be continued from any of the previous cycles that have been performed The user specifies a restart run through the Job Information Dialog Box and the modeler automatically pulls the chosen scantlings from the restart file To make a restart run open the Job Information Dialog Box and check the Scantlings Available box as shown in the next figure This will cause the Restart box to be changed from gray to white and you can enter the starting cycle For example the next figure shows that the second run will started from the latest cycle 3 design Enter the number of new design cycles in the Design Cycles box In the next figure a further two cycles are specified plus an evaluation cycle MAESTRO Job Information General Structure Origin amp Balancing Units Criteria Comments Job Title noge Job Type Analysis Optimization r Save Deflections Design Cycl Piip Deflections Available Preliminary Cycles V Final Evaluation Strake Opt Cycles 0 Jv Save Scantlings Restart Cycle M Scantlings Available Output Level Normal Extended LevelforLast 0 cycles C Ex
139. cale for the graphical representation of pressure will remain the same if switching between load cases unless the maximum pressure value is higher than the current scale s maximum value To view the load case specific legend turn off the pressure view and then turn it on again Immersion Volume Inverse Linear Pressure Surface Head Surface Zero Additional Beam Edge Al Immersion This option will display the pressure on the wetted panel elements based on the initial location of the model s waterplane for the currently selected load case 3 49E 000 3 22E 000 2 95E 000 2 68E 000 2 42E 000 2 15E 000 1 88E 000 1 61E 000 sat 13464000 won LTH Lf 1 07E 000 2 68E 001 0 00E 000 The dynamic query icon mr can be used to query an element to recover the pressure and double clicked to echo the information to the output tab 2009 DRS Defense Solutions LLC Advanced Technology Center General 67 Volume Inverse This option will display the pressure due to all volume loads on the inverse side of the plate so that the pressure display can be seen easily The dynamic query icon canbe used to query an element to recover the pressure and double clicked to echo the information to the output tab Linear Pressure This option will display the pressure of the panel elements for which a linear pressure is defined for the currently selected load case The dynamic query icon c
140. case The CK Tip Over button will check to see if any of the bay sets are tipped over 2009 DRS Defense Solutions LLC Advanced Technology Center 216 MAESTRO 9 0 7 7 4 4 Acceleration Tab LoadCase II v Name z General Acceleration Mass Point Force Pressure Balance Acceleration Reference Point C CenterofFlotation x m Center of Gravity Y m User Defined Z m Additional Acceleration Value fe Ship Coordinate System C World Coordinate System X Surge fo m s 2 ThetaX Roll oC rad s 2 Y Heave g mjs 2 ThetaY Yaw fo rad s 2 Sway fo m s 2 ThetaZ Pitch 0 rad s 2 The Acceleration tab can be used to apply an additional acceleration to the model The acceleration can be applied at the center of flotation center of gravity or at a user defined location The center of flotation and center of gravity values are automatically calculated The acceleration can be applied to all 6 degrees of freedom in the ship or world coordinate system The acceleration units and reference point length units are regarded as those defined in the Units dialog 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 217 7 4 5 End Moments Tab LoadCase x Name General End Moments Mass Point Force Pressure Balance A sagging bending momentis positive A hogging bending momentis negative Shear force is positive upwards at b
141. ce system This mesh is generated by specifying the location of endpoints in a transverse plane at both ends of the module These end planes are called the reference plane and the opposite plane The program then creates a node at each user defined section location between the reference and opposite endpoint Once the nodal mesh has been defined strakes are then created by specifying the pair of endpoints that are in line with the sides of the strake Strakes and sections are numbered sequentially as are the intervals between the sections The program uses the terms strake endpoint section and module to refer to locations within the structural model For example the first panel in the keel strake is located at strake 1 section interval 1 Each strake extends for the full length of the module and has uniform scantlings However shorter strakes and changes in scantlings can be obtained by assigning two or more strakes to the same pair of endpoints and then selectively deleting portions of each Also various combinations of scantlings can be obtained by deleting the unwanted strake elements and inserting additional elements in their place MAESTRO provides an element deletion feature that makes this relatively easy Frames need not occur at every section they can occur at every other section specific sections only or not at all The total length between frames is referred to as a bay This means that each structural panel which by d
142. ce the optimum number of stiffeners in each strake of plating 2009 DRS Defense Solutions LLC Advanced Technology Center Tutorials 327 These coefficients might vary according to which shipyard is building the ship For example one shipyard might have more automatic welding machines so that its cost per unit length of stiffener weld might be cheaper than at another shipyard In this case the optimum design would probably have more stiffeners and less steel than at another shipyard with higher welding costs Note that for optimization there is no need for absolute values for the coefficients they need only have the correct relative magnitudes In this example the cost unit is K DOLLARS 1000 but this is arbitrary The volumetric cost coefficient will therefore be in units of K DOLLARS per in Let us say that a rough order of magnitude figure for steel cost including handling and other costs that are related to the amount of steel is 1 75 per pound Translating to the example units gives 0 50 per in or 0 0005 K DOLLARS per ini Similarly let us say that a rough order of magnitude figure for welding costs is 6 00 per inch of weld which is 0 006 K DOLLARS per inch These values are inserted as the volumetric and lineal cost coefficients in the first page of the Dialog Box The cost function allows for different values to be used for rolled panel line members plating and stiffeners and fabricated members fra
143. cedure for creating Additional Nodes 1 Make sure the appropriate module is set as the current part and launch the Additional Nodes dialog from the Model gt Nodes gt Create Modify gt Add l Node menu or from the toolbar Reference Points EndPoints Additional Nodes m Cartesian C Cylindrical X in Y in Z in Coordinate P P f P P Create Modify Delete Close 2 Click the ID button to get the next unique ID for the new additional node 3 Type in the coordinate values or snap to a point in the model by clicking in one of the coordinate boxes and the clicking the point in the model 4 Click the Create button This same procedure can be repeated for more additional nodes Creating Construction Geometry Menu Tools gt Construction Geometry gt Mouse Hold Ctrl key amp Right Click MAESTRO s construction geometry can be very helpful in defining EndPoints and additional nodes 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 155 This tutorial shows the procedure for creating two construction lines and a construction marker at their intersection A description of each type of construction geometry can be found below 1 Open the construction geometry dialog box from the Tools gt Construction Geometry gt menu or by holding the Ctrl key and right clicking in the modeling space Repeat CMarker gt CLine gt De
144. ceive the positive normal side In conjunction with the Element Normal Side view the user can use the Dynamic Query tool which can be initiated via the liceon to reverse the element normal To use this functionality the user must first change to the Element Normal Side view toggle the 2009 DRS Defense Solutions LLC Advanced Technology Center 48 MAESTRO 9 0 7 Dynamic Query icon move the mouse cursor over a particular element right click the mouse and finally select the menu item Element Pressure Side The figure below shows how MAESTRO distinguishes between a positive and negative pressure face The pink face of the element will receive the positive pressure In conjunction with the Element Pressure Side view the user can use the Dynamic Query tool which can be initiated via the LM icon to reverse the element normal To use this functionality the user must first change to the Element Pressure Side view toggle the Dynamic Query icon move the mouse cursor over a particular element right click the mouse and finally select the menu item Stiffener Side The pink face designates the stiffener side of the plate element In conjunction with the Stiffener Side view the user can use the Dynamic Query tool which can be initiated via the ibd icon to Flip Stiffener Side With this view displaying toggle the Dynamic Query icon move the mouse cursor over a particular element right click the m
145. chnology Center 114 MAESTRO 9 0 7 Zoom In Zoom Out Fit Pan Last Body Plan Plan View Profile View SouthEast SouthWest NorthEast NorthWest v Perspective Element Type Copy View Named View Parts Tree Area When the cursor is located in the Parts Tree area the user can access a parts quick menu This menu allows the user to set part attributes modify parts and query parts as shown below Set Current Part Set View Part Rename Copy Mirror Delete Add Mirror Set Visibility On Set Visibility Off Visibility List Set Transparency On Set Transparency Off Show Weight Groups Tree Area When the cursor is located in the Groups area the user can access a groups quick menu This menu allows the user to set group attributes modify groups and query groups as shown below 2009 DRS Defense Solutions LLC Advanced Technology Center General 115 Set View Part Set Visibility On Set Visibility Off Context Default Color Context UserDef Color Free Edges Rename Copy Delete Command Line Output Window and Grid Window When the cursor is inside the area of one of these tabs which are located at the bottom of the MAESTRO GUI the right click will access various quick menus These quick menus are shown below Find Cut Copy Paste Ctrl V Undo Last Clear All Save T F Save AS ney CoC Show Current View Open Paste Show All Parts Print Cha
146. cking on File gt Analysis Evaluation gt Legacy Version of MAESTRO gt Optimization Settings Group Optimization Settings Overall Defaults Constraints Structure Method C Genetic Seq Linear Prog 2 Scalable Solver Standard Default Constraint Set 0001 Default Min Max Values Variable Min As Model Max As Model Min New Limits Max New Limi Thickness in 0 375 0 4375 0 125 1 Spacing 0 0 Number Strake 4 4 10 Web Height in 6 6 10 Web Thickness in 0 25 k 0 6 Flange Width in 4 10 Flange Thickness in 0 25 1 Web Height 15 30 Web Thickness in 0 375 1 Flange Width in 8 16 Flange Thickness in 0 75 1 Web Height 18 Web Thickness in 0 375 Flanne Wiidth fin a cse This picture shows the Overall Defaults page which defines the overall information and Constraint Set 1 which specifies the default Min Max constraints 2 2 1 Type of Optimization 2009 DRS Defense Solutions LLC Advanced Technology Center 324 MAESTRO 9 0 7 Group Opt Settings ID 1 v General Group STANDARD v Optimization Type v Output Level D v Discretization On Reference Values Cost 131 7 Weight 15 02 Multi Objective Weighting Cost 50 Weight 50 Cost Coefficients Stiff Panel Volume 00005 Stiffener Length 0 006 Girder Frame Yolume 00005 Girder Frame Length 0 006 The Standard D
147. components can be evaluated namely vertical bending horizontal bending section shear and torsion e Fabrication related initial imperfections in the form of initial deflections and welding residual stresses are dealt with as parameters of influence e Aged related structural damages such as corrosion either general or localized corrosion fatigue cracking and local denting are dealt with as parameters of influence e Accident induced structural damages caused by collision grounding fire and explosion are dealt with as parameters of influence Nastran Translator This module automatically translates either the entire MAESTRO finite element model or a portion thereof into Nastran Alternatively Nastran models can be translated into MAESTRO as fine mesh modules ANSYS Translator This module automatically translates either the entire MAESTRO finite element model or a portion thereof into ANSYS 2009 DRS Defense Solutions LLC Advanced Technology Center Introduction 17 3 1 2 Finite Element Modeling The first step in the finite element process is creating the model which consist of nodes and finite elements In MAESTRO the mesh is created by introducing reference points which consist of endpoints and additional nodes These reference points are either created manually by specifying the global coordinates or by importing existing geometry via dxf or idf file which is then used as construction geometr
148. constraints from the View gt Constraints menu option Tools amp View Style Viewports This section of the View Options dialog allows the user to switch between a single split or 2009 DRS Defense Solutions LLC Advanced Technology Center 118 MAESTRO 9 0 7 four view workspace For more detailed information on these views please see the Workspace Layout section Video Driver Options The recommend settings in the View Options dialog are Rendering Options Hardware Z buffer Video Driver OpenGL Driver Driver Options Double Buffering The Video Driver and Driver Options can be found by clicking the Advanced tab in the View Options dialog Advanced View Options Video Driver C Microsoft Windows Driver fe OpenGL Driver Driver Options M Double Buffering Backing Store Mouse Selection Proximity 2 mm The Tools amp View Style sections also allows the user to select between a variety of viewing options and whether construction geometry cutting planes and the world axes are visible Plot Legend This section allows the user to change the default settings of the legend when plots are shown Pre Post processing Deformation Scale The deformation scale allows the user to adjust the magnitude of the deformed model view Note the model must be in a deformed view to adjust the deformation scale 2009 DRS Defense Solutions LLC Advanced Technology Center General 119
149. cost reduction and weight reduction are given equal importance In the Dialog Box they are specified as percentages 2 2 2 Discretization MAESTRO provides a feature whereby the designer can specify a list of standard or available thicknesses the criteria as to how round off is to be done for the various member types and the desired or permissible increments in web depths and flange breadths of the various member types During the optimization process the design variables are treated as continuous variables in order to avoid the high computational cost of discrete variable optimization But when the design is seen to be converging the designer can specify that the next run should include discretization of the design variables In that run the discretization will be done during the last of the design cycles requested for that run The discretization is not simply a rounding up all of the design variables to the next standard size 2 2 3 Cost Function For structural optimization the only costs that are relevant are those that are influenced by scantlings The two types of cost that are most directly related to scantlings are the cost of materials and the cost of fabrication and for these MAESTRO provides the following general purpose cost function NS Cost D Cy C Cr where NS number of strakes and all of the four cost terms are on a per strake basis Stiffened Panel Cost C cost of the stiffened panel for each strake I
150. covered in each element match exactly to the theoretical values Element 1 axial stress 500 00 psi Element 2 axial stress 666 67 psi 2009 DRS Defense Solutions LLC Advanced Technology Center 370 MAESTRO 9 0 7 Model rodtest mdl 11 3 Added Mass Panel Method for Added Mass 1 Basic Theory The added mass can be expressed as mt oknkds k I Surge 2 Sway 3 Heave D n n n n Where gt is the unit normal vector on the body surface k P is the solution of the following problem 2k _ VE 9 in the field 2 k grado n JOT Sys On 3 The solution to the Laplace equation 2 is obtained by covering the body surface with local source strengths 56 15 at point q61 S Thus the velocity potential can be expressed as k _ k E karaka k k _ p p p x y z ffo G p g ds ff o 6n G x y z 6 n 6 ds k 1 2 3 3 1 1 G p q G x y 2 6 7 6 in which S 4n p x y z G amp n 6 2009 DRS Defense Solutions LLC Advanced Technology Center Verification and Validation 371 Fig 1 According to boundary condition 3 the normal velocity of the fluid at the surface of the body can be solved by pt p a om en D Op p se SX p Ifo i q n p e VG p q ds n k 1 2 3 n 2 4 2 Panel Method The problem to determine the continuous function x y z is replaced by the problem to determine a finite number N of value 14 12 3 4 N The
151. covered modeler file e How can download the latest version of MAESTRO The latest version of MAESTRO and the security driver can be downloaded from http www orca3d com maestro download htm Note you must have a valid maintenance and support expiration date to run the newest release of MAESTRO e Where can find additional support for MAESTRO In addition to contacting technical support at maestrosupport orca3d com you may visit the MAESTRO forum at MAESTRO Forum to add and review posts from MAESTRO users and technical support personnel e Why aren t MAESTRO folders removed from Start gt All Programs when MAESTRO is uninstalled This is due to the autosave files that are added to the directory These folders and menu items can be manually deleted after the uninstall process 2009 DRS Defense Solutions LLC Advanced Technology Center Frequently Asked Questions 383 12 2 Pre Processing e How do the stiffeners in a stiffener layout differ from a beam element Stiffeners are defined as beam elements but they are not actual finite elements in a coarse mesh model Instead they are treated as additional stiffness in the defined direction for the panel element they are defined on thus converting the material to orthotropic In a coarse mesh model all stiffeners are treated as internal regardless of their defined location The number of stiffeners whether defined as internal or edge is the key to how
152. cture having the following properties e It has one direction regarded as its lengthwise direction along which there are regularly spaced transverse planes or sections which constitute either the locations or the boundaries of some or all of the individual structural members e Within each transverse section the layout of the members is similar and in the lengthwise direction the geometry of each section is either constant or linearly varying depending on the endpoint definitions e Members that occur repeatedly tend to have the same local structural dimensions that is plate thickness and flange and web widths and thicknesses These are sometimes referred to as scantlings Because of a module s geometric regularity and uniformity of scantlings in the lengthwise direction it is convenient to regard a module as being made up of strakes As shown in Figure 3 a strake is a lengthwise row of stiffened panels and frame segments and optionally a longitudinal girder along one edge The location of beams and panels is not limited to strakes they can also be inserted individually at other locations and at various orientations 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 133 bbs of stiffeners M Strake no Section no Figure 3 MAESTRO Terminology Each module has its own three dimensional nodal mesh defined within the module s referen
153. curve is almost linear whereas for a thick plate it approaches the Von Mises ellipsoid The partial safety factor varies between ys and y depending on the stiffening and on the relative values of R p and Ryp For unstiffened panels yc is used For a stiffened panel if the transverse stress is zero or tensile use gs otherwise use a value between ys and yc according to the value of R p relative to R p if the former exceeds the latter a warning is issued that the stiffener orientation appears to be inefficient Girder Failure Modes MAESTRO s limit states for girders cover 7 different modes of failure The table below provides a summary of these failure modes Girder Failure Modes GCT Girder Collapse Tripping GCCF Girder Collapse Compression in Flange GCCP Girder Collapse Compression in Plate GYCF Girder Yield Compression in Flange GYCP Girder Yield Compression in Plate GYTF Girder Yield Tension in Flange GYTP Girder Yield Tension in Plate Girder Failure Modes Collapse Collapse limit states are defined when the structure or member has failed in its primary load carrying role Girder Collapse Tripping GCT This collapse mode is similar to the PCSB It is a complex phenomenon and not many authors have addressed this problem Reference can however be made to the paper in Ref 17 which deals with the elastic tripping modes of a girder While developing the MAESTRO model for the girder collapse modes the scant
154. d elements Optimization The MAESTRO Optimization module uses sequential linear programming to redesign the structure This optimization eliminates any structural inadequacies while achieving an optimum design based on user specified objectives goals which may be least weight or least cost or even both of these in a weighted non dimensional combination In its optimization mode MAESTRO iterates the structure through design cycles in which it revises scantlings reruns the finite element analysis and reevaluates the structural adequacy of each member for all failure modes and load cases This iterative process continues until the structure has converged to an optimum design that has no structural inadequacies ALPS ULSAP Analysis of Large Plated Structures Ultimate Limit State Assessment Program The ALPS ULSAP module is for the Ultimate Limit State Assessment for welded steel or aluminum stiffened panels under combined in plane and lateral pressure loads at quasi static or impact action situations The main features of this module are as follows Paik Thayamballi e Ultimate limit state or ultimate strength assessment of stiffened panels e Unstiffened plates uniaxially stiffened panels and orthogonally cross stiffened panels grillages can be examined e Six types of collapse modes are examined namely overall collapse biaxial compressive collapse beam column type collapse stiffener web buckling stiffener tripping and gr
155. defined in Constraint Set 2 The acronym button at the lower right of the Dialog Box provides a pop up list that explains the various acronyms TPL Plate Thickness STF Number of Stiffeners BBS Breadth Between Stiffeners HSW Stiffener Web Height TSW Stiffener Web Thickness BSF Stiffener Flange Breadth TSF Stiffener Flange Thickness HGW Girder Web Height TGW Girder Web Thickness BGF Girder Flange Breadth TGF Girder Flange Thickness HFW Frame Web Height TFW Frame Web Thickness BFF Frame Flange Breadth TFF Frame Flange Thickness ZMOD Section Modulus of Module IMOD Moment of Inertia of Module In this example the minimum values of flange width 8 inches for the frames and 9 inches for the girders are chosen not because of fabrication but rather to prevent flexural torsional or lateral torsional buckling for these members This is more than just a local type of failure and in the future it will be added to those limit states which are examined explicitly by MAESTRO The stipulation of a minimum value which might depend on the member length and other factors is more typical of code based design and this example shows that if desired the requirements of such codes can be incorporated into the constraint set 2009 DRS Defense Solutions LLC Advanced Technology Center Tutorials 329 2 4 Optimization Dialog Box Page 2 Other Constraint Sets The first page Overall Defa
156. dify gt EndPoint from the menu This icon launches the Additional Nodes dialog It is the same as selecting Model gt Nodes gt Create Modify gt Additional Node from the menu This icon launches the Strakes dialog It is the same as selecting Model gt Elements gt Create Modify gt Strake from the menu This icon launches the Compounds dialog It is the same as selecting Model gt Elements gt Create Modify gt Compound from the menu This icon launches the Finite Element Quad dialog It is the same as selecting Model gt Elements gt Create Modify gt Quad from the menu amp This icon launches the Finite Element Triangle dialog It is the same as selecting Model gt Elements gt Create Modify gt Triangle from the menu Y This icon launches the Finite Element Beam dialog It is the same as selecting Model gt Elements gt Create Modify gt Beam from the menu lt This icon launches the Finite Element Rod dialog It is the same as selecting Model gt Elements gt Create Modify gt Rod from the menu This icon launches the Finite Element Spring dialog It is the same as selecting Model gt Elements gt Create Modify gt Spring from the menu This icon launches the Finite Element RSpline dialog It is the same as selecting Model gt Elements gt Create Modify gt RSpline from the menu 4 This icon launches the Finite Element Bracket dialog It is the same as selecting Model gt Elements
157. dition the way a support node handles mass may change between load cases This simulates the case of containers particularly which are constrained by cell guides and one way attachment devices NOTE The defined centroid and gyradii are not carried over in a Natural Frequency Analysis 1 Begin by opening the groups dialog box using the Groups gt Bay menu option or from the toolbar Groups Volume Plate Module Section Node Bay General Corrosion Name gt Centerline Group Sets Color Create Del tem Close 2 Click the ID button to assign a unique ID to the bay group 3 Type a descriptive name into the Name box 4 Click Create 5 Click Add Set You can then give the set a name mass centers of gravity and radii of gyration 6 Click in the lower window and then select nodes from the model to add to the set 7 The columns for X X Y Y Z and Z are used to define whether the corresponding node can receive force in that direction due to an additional acceleration designated either with a Y for yes or N for no 8 Click Modify to save the changes 2009 DRS Defense Solutions LLC Advanced Technology Center 194 MAESTRO 9 0 7 Sample bay set input data can be found in the Models and Samples MAESTRO installation directory as BayAcceleration mdl and BayBalance mld General Group The General groups dialog is a convenient way for the user to creat
158. e sparse symmetric and non symmetric linear systems of equations on shared memory multiprocessors The solver uses a combination of left and right looking Level 3 BLAS supernode techniques 11 In order to improve sequential and parallel soarse numerical factorization performance the algorithms are based on a Level 3 BLAS update and pipelining parallelism is exploited with a combination of left and right looking supernode techniques 6 7 8 10 The parallel pivoting methods allow complete supernode pivoting in order to compromise numerical stability and scalability during the factorization process 13 Iterative Solver MAESTRO s iterative solver method uses Intel s iterative sparse solver which is based ona reverse communication interface This scheme gives the solver great flexibility as it is independent of the specific implementation of operations such as matrix vector multiplication 14 When this solver is selected the user can choose a maximum number of iterations to perform and a tolerance The analysis will complete whenever the number of iterations or tolerance is met The iterative solver is mostly used for large models that are unable to be solved using the sparse solver Skyline Solver MAESTRO s Skyline solver is an in house sparse solver with the matrix stored using the skyline storage scheme This solver is an alternative or backup to MAESTRO s Sparse solver and is less efficient The benefit of the Skyline solver is that
159. e a collection of elements for viewing areas of interest The General groups is also used create a General group which can then be refined for fine meshing or simply used for viewing this particular area of interest A general group can include any type of elements 1 Begin by opening the groups dialog box using the Groups gt General menu option or from the toolbar Groups Volume Plate Module Section Node Bay General Corrosion vy Name ii O Centerline Group Full Strake Full Compound Whole Module Select By Box Module Name Color Create Del Item Close 2 Click the ID button to assign a unique ID to the general group 3 Type a descriptive name into the Name box 4 Check the Centerline Group if the general group spans the centerline of a half model This will automatically combine the mirrored group into one single group if the model is mirrored 5 Checking the Full Strake Full Compound box will include the entire strake or compound as the part of the general group by clicking on any part of it 6 Checking the Whole Module box will include all elements of the module by clicking any part of it 7 Click inside the main white part of the dialog box and then select the elements that make up general group The Select By Box option can be checked to use a box window to add all 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 195 the
160. e default is 0 25 To switch off discretization for HSW and BSF specify a value of 1 for this item 2009 DRS Defense Solutions LLC Advanced Technology Center Tutorials 357 ITEM 4 ITEM 5 ITEM 6 ITEM 7 ITEM 8 Girder roundoff fraction GIRROF for the web height HGW and flange breadth BGF of the girders This item is identical to Item 3 except that this value is applied to the girders The default value is 0 25 To switch off discretization of HGW and BGF specify a value of 1 for this item Frame roundoff fraction FRMROF for the web height HFW and flange breadth BFF of the frames This item is identical to Items 3 and 4 except that this value is applied to the frames The default value is 0 25 To switch off discretization of HFW and BFF specify a value of 1 for this item Dimensional increment PNDELT for the web heights and the flange breadths of the panel stiffeners If the Nth discrete value of the web height is HW N then the N Ist value is defined as HW N 1 HW N PNDELT Note that this item has dimensions so the appropriate units as previously defined must be used The default value is 10 0 for mm 0 010 for m and 0 25 for inches Dimensional increment GRDELT for the web heights and flange breadths of the girders This item is similar to Item 6 except that this value applies to girders The default value is 20 0 for mm 0 020 for m and 0 5 for inches Dimensional increment FRD
161. e following 9 steps If you actually perform these steps you will be generating a new fourth line of data and the 10 step will Remove it 1 Click on Add A new blank line appears in the List Box 2 Click in the Coef 1 cell and type in 0 7 3 Double click in the first Variable cell to get a drop down list of variables Scroll down and select HFW 4 Define the first operator You can toggle through the three operators by double clicking Double click on the symbol to change it to 5 Double click in the second Variable cell to get a drop down list of variables Scroll down and select HSW Click in the Coef 2 cell and type in 1 Go to the second operator cell toggle double click until you get the gt symbol Click in the RHS cell and type in 1 Click on Modify 0 Since we don t want this line click on Remove gt OND 2 5 Data Concerning Module Related Load Effects 2 5 1 Module Level Design Limits Constraints As shown in the next figure this example contains two constraints that pertain to the entire module rather than to an individual strake 1 Minimum required value of moment of inertia of the module MIN IMOD Here the limit or constraint is some maximum permissible value of module deflection due to vertical bending Such a limit is unlikely to be relevant for a pontoon but naval vessels can have such limits arising from radardirected guns and in aircraft structures such limits are universal and are dominant i
162. e is to be appropriate to the operating system Text strings may be up to 79 characters long and are limited to ASCII characters 1 through 127 Units Units must be specified as either SI or User Defined If User Defined then the following lines must be given of user units meter of user units square meter of user units cubic meter of user units kg Some entities may not require all of the conversion factors and the entity s definition will specify which should be included 2009 DRS Defense Solutions LLC Advanced Technology Center 392 MAESTRO 9 0 7 Coordinate System Since different programs use different coordinate systems e g some have positive X aft some have positive X forward some use Z for the longitudinal coordinate etc the coordinates of a fixed point in space is required This point is one unit forward of the origin one unit to starboard and one unit down from the origin Then as data is read in from the file by multiplying the data by the given vector and by your own vector the sign will be correct All data in the formats is given in the order longitudinal athwartships and height Not all entities will have a coordinate system associated with them If not the entity definition will leave this section out Data Tags Data tags e g ENTITY while not absolutely required in a fixed format file make the file easily human readable and can simplify the computer reading pr
163. e masses may be known or estimated only in the form of a one dimensional distribution along the length of the structure and the Section mass option is intended for this and only this because it is very approximate Here the user can add Section Interval groups that were previously created using the Groups dialog to the current load case definition These previously defined section groups are made available to the user via the drop down menu 2009 DRS Defense Solutions LLC Advanced Technology Center 212 MAESTRO 9 0 7 Note The values of the section groups can only be changed via the groups dialog LoadCase Name General Acceleration Mass Point Force Pressure Balance Volume Module Section Node Plate Bay 0 Add Use group dialog to change data Length mm Mass per Len gt Modify Del Row Close Help Once a section group is selected from the drop down menu click Add The section interval length mass length and mass values are updated from the section definition but these values can only be changed using the groups dialog Node Mass The Node mass option offers the user a method to generate a specified amount of additional non structural mass and allocate it equally among the nodes defined in the nodal group The user can add Nodal groups that were previously created using the Groups dialog to the current load case definition These previously defined nodal
164. e middle Therefore FYCF2 means that the relevant location the place where the total compressive stress axial bending in the frame flange has reached approximately the maximum permissible value of y 1 25 is at strake edge 2 Since there is a bracket at this edge the precise location is at the toe of the bracket The required information can be obtained from the evaluation cycle output for strake 1 pages 49 to 52 For example the summary on page 52 shows that for the FYCF2 limit state the relevant section is section 2 and the relevant loadcase is 2 Turning 2009 DRS Defense Solutions LLC Advanced Technology Center Tutorials 343 back to this section and loadcase on page 50 the value of the bending moment at the bracket toe at strake edge 2 the second of the three values is seen to be 3 778E05 The bending moment value at the far right MFBKT2 is the value at the junction of the flexible length and the rigid length see Section 8 6 of reference 1 This is larger than the value at the bracket toe but since it is within the bracket it is not used in optimizing the frame But it is supplied by MAESTRO so that it can be used later in designing the bracket The output also gives the frame stresses The stress in the frame flange axial bending is ASIGFF2 11 230 psi and the shear stress in the web is TAUF2 12 320 psi Together these cause the frame flange to be just at the maximum allowable stress condition wh
165. e topics in this section provide detailed information on the MAESTRO functionality used during the model checks stage of an analysis Defining Constraints Toolbar Menu Model gt Define Constraints Constraints are used to restrict the model s movement in any of the 3 translational or 3 rotational degrees of freedom The following tutorial shows how to define constraints for a model 1 Begin by opening the constraints dialog by using the Model gt Define Constraints menu option or from the toolbar Constraints Summary General Boundary Module First Module Second Module Legend Translation Fixed Translation Forced Disp Rotation Fixed Rotation Forced Disp 0 Center Plane Node Total Number of Restraint Nodes 0 Cancel Help The first tab in the dialog gives a summary of the constraints The legend gives the graphical representation when the view constraints option is selected This can be chosen from the View gt Constraints menu option The magnitude of the constraint marker can be adjusted in the View Options dialog If only a small portion of the ship has been modeled the user can define boundary conditions at the vessels ends by selecting the First Module and Second Module This is 2009 DRS Defense Solutions LLC Advanced Technology Center 180 MAESTRO 9 0 7 6 2 useful for preliminary evaluation of the ship s structure 2 Click the Ge
166. e use of this functionality will be discussed below EndPoint Additional Node Strake Quad Triangle Beam Rod Spring Compound EndPoint Creation To create an Endpoint using the Quick Element Creation method it is important to note that the user must first define construction markers Without construction markers this functionality will not work Select the Endpoint option from the drop down menu The user can now single click on the first construction marker in the model that is to become the endpoint s reference end and then double click on the construction marker that will become the endpoint s opposite end Repeat this process for as many endpoints as you wish After completing the Quick Creation sequence there are two important things to remember The first is to toggle off the quick creation icon and second the Quick Creation process 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 175 does not update the ID numbers in the dialog box Therefore if you are going to continue using the dialog box you must close the Reference Points Dialog Box and the reopen it Additional Node Creation To create an Additional Node using the Quick Element Creation method it is important to note that the user must first define construction markers Without construction markers this functionality will not work Select the AddNode option from the drop down menu The user c
167. e user to change the default values of the station spacing and 0 location for longitudinal hull plots Safety factors for panel girder and frame elements can be set by clicking on the associated button 5 3 Defining Units 2009 DRS Defense Solutions LLC Advanced Technology Center 136 MAESTRO 9 0 7 Menu File gt Units The Units dialog box can be accessed from the File gt Units menu Parameter Data Conversion to SI Length 0 0254 Area 0 0006451 Volume 1 63871e 0 Inertia 4 16231e 0 Force 4 44622 Weight Force 0 453592 Pressure Stress 6894 76 Acceleration 0 0254 Treatdensityas Force Choose Standard Unit Systems lbf lbf v in s 2 v per unit volume v Set Parameter Data Canet Individual parameters can be changed using the Label drop down boxes or a Standard Unit System can be chosen from the drop down box The Set Parameter Data box must be clicked for the units to change The seven Standard Unit Systems available are e SI N m Newtons and meters e SI N mm Newtons and millimeters e SI MN m MegaNewtons and meters fps Feet pound force and seconds mks Meters kilogram force and seconds cks Centimeters kilogram force and seconds ips Inches pound force and seconds 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 137 5 4 Defining Parts RE CE Men
168. ectangular plate of a given aspect ratio The plate is tested separately for each of the two types of loads a uniform pressure of 1 0e 4 and a central concentrated load of 4 0e It is tested for two types of boundary 2009 DRS Defense Solutions LLC Advanced Technology Center 364 MAESTRO 9 0 7 conditions simply supported edges and clamped edges and two aspect ratios yielding a total of eight test problems The results are presented in Table 1 showing that the MAESTRO QUAD4 element gives quite good results The two models are presented in Figures 1 and 2 Because of symmetry only one quarter of the plate is modeled for each aspect ratio b gt Figure 1 Rectangular Plate Aspect Ratio 1 a 2 0 b 2 0 t 0 0001 E 1 7472e07 v 0 3 I a e a y Figure 2 Rectangular Plate Aspect Ratio 5 a 2 0 b 10 0 t 0 0001 E 1 747287 v 0 3 BCs Aspect Loads Theoretic MAESTR MAESTR MSC Nas MSC Nas _ Input Ratio al O Solver O tran tran ErrorlData Files Deflection Error 2009 DRS Defense Solutions LLC Advanced Technology Center Verification and Validation 365 Oo D A o1 D D CO o gt Pressure 1 Point Load Pressure 5 Point Load Pressure N EN de I ho Clamped All Sides Oo spl cipt mod spl4clpt f 06 oo A oO 5 P Table 1 Rectangular Plate Results 2009
169. ed MAESTRO will run in Demo mode with limited functionality If you would like to purchase a license or renew an existing license you can go to http www orca3d com maestro purchase htm to fill out a form for a quotation or email directly to sales orca3d com with your inquiry If you experience any problems during or after the installation click Help gt Technical Support from the menu to send an email to support maestro com Note for Network Locks If you are troubleshooting issues with a network lock you may refer to the ReadMe pdf file located in the MAESTRO installation directory under MAESTRO System Sentinel or see the Security Devices section of the help manual 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 General General 25 4 General The topics in this section provide an overview of the MAESTRO program user interface 4 1 Workspace Layout The MAESTRO Modeler is a tool for creating a structural model through a graphical user interface GUI With the help of various menu options and toolbars the user can rapidly generate a large yet accurate model The layout of the MAESTRO GUI is shown below The main display area contains the graphical representation of the model geometry It is used for viewing either the entire or a portion of the current structural model and is often used to make interactive selections The main display can have several layouts inc
170. ed or strakes not defined as side or bottom will disappear 3 Elements improperly defined can be changed from wetted to not wetted or vice versa by clicking the dynamic query icon 7 4 Highlight the element to change and right click with the mouse and check or uncheck Wet accordingly 5 Uncheck View gt Wetted Elements from the menu to return to the element type view Menu View gt Plate gt Element Pressure Side 1 This integrity check can be performed from the View gt Plate gt Element Pressure Side menu option 2 All elements in the current view will be given a pink pressure side and gray non pressure side 3 This provides a quick graphical check on the hull pressure side as well as to verify a common convention was used for defining interior structures 4 The dynamic query t v can be used to switch the pressure side of an element by right clicking and selecting Normal Reverse 5 Select View gt Element Type from the menu to return to the element type view Menu Tools gt Integrity Check gt Aspect Ratio 1 This integrity check can be performed from the Tools gt Integrity Check gt Aspect Ratio menu option 2009 DRS Defense Solutions LLC Advanced Technology Center 182 MAESTRO 9 0 7 2 A dialog box opens allowing the user to set the maximum allowable aspect ratio the default value is 4 0 3 If there are no elements exceeding this aspect ratio a di
171. ed allowable values If no roundoff of strake variables is desired there is no need for this data line But once the DISCRETIZE data has been created adding the two letter prefix is a convenient way of switching off the roundoff feature and avoids having to remove or comment out the data for it ITEM2 The number of discrete plate thickness values These values will be used for the strake plating and also for the webs and flanges of the stiffeners girders and frames ITEM3 Type of roundoff Normally the roundoff is done progressively modifying only a few design variables at a time in order that a decrease in a design variable can be compensated for if necessary by an increase rounding up of a subsequent design variable This is the default and will be done unless it is overridden by entering the keyword SIMPLE for this item In that case the program simply rounds off all design variables simultaneous ly according to the roundoff fractions A null or any other entry will give the ordinary progressive roundoff ITEM 4 Debug output flag A 1 will produce additional output during the roundoff process This item should normally be null or zero 2009 DRS Defense Solutions LLC Advanced Technology Center 356 MAESTRO 9 0 7 SECOND LINE ITEMS 18 The first eight plate thickness values in order of increasing plate thickness THIRD LINE ITEMS 18 etc The next group of eight plate thickness values
172. ed in the file as LWL 451 5 As many entries as desired may be made in this form using the ITTC ISTS standard computer symbols NOTES ON THE IDF HYDRO ENTITY The HYDRO entity of the IDF file is used to pass parametric information about hull geometry between programs This information length on waterline displacement volume and trim for example is representative of a single vessel load condition The symbols are derived from ITTC computer symbols and terminology In January 1993 the ITTC Symbols and Terminology Group identified the need for an Interim Standard Transfer Set ISTS as a subset to their comprehensive database oriented collection of computer symbols Dr Bruce Johnson Chairman has asked IMSA to prepare and define the ISTS The symbols used in the IDF HYDRO entity will form the ISTS To eliminate redundancy and potential confusion the ISTS philosophy will be to use only those symbols based on geometric items displaced volume for example rather than parameters such as Cb Also a number of geometric and conversion references are defined Abbreviations used in this document FP forward perpendicular Reference datum for the forward point of the length between perpendiculars LPP AP after perpendiculars Reference datum for the aft point of the length between perpendiculars LPP MIDP midship Located midway between FP and AP References International nautical mile 6076 1155 feet 1852 00 meters
173. een stiffeners 12 The user can also define if there is an Edge 1 or Edge 2 stiffener 13 Click Create and then click Close to return to the MAESTRO Strakes dialog box 14 Select the new Stiffener Layout from the drop down menu 15 Click the Deletions tab and check if any of the strake sections should have deleted plate frame or girder elements 16 Click Create 5 12 Creating Additional Elements Quick Reference Creating Quads Creating Triangles Creating Beams Creating Rods Creating Springs Creating RSplines Creating Brackets 2009 DRS Defense Solutions LLC Advanced Technology Center 160 MAESTRO 9 0 7 In addition to strakes MAESTRO has the ability to create individual panel elements as triangles or quads depending on the number of nodes used to define the element beam elements and rod elements EAG Menu Model gt Elements gt Create Modify gt Quad This tutorial shows the procedure for creating an individual quad element 1 Begin by opening the Finite Element Quad dialog box using the Model gt Elements gt Create Modify gt Quad menu or from the toolbar Finite Elements E Springs Rods Beams Triangles Quads RSplines Brackets El Connectivity Node 1 Node 2 Node 3 Node 4 Property amp Stiffener Layouts Property ID Layout Nul Stif Layout z mfo x Direction Edge 1 to Edge 3 w Side linside Wetted Rever
174. ef 1 and type in 1 3 Double click in the first Variable cell to get a drop down list Scroll down and select MIN IMOD Double click on the gt symbol to change it to Click in the RHS cell and type in 300000 Click on Modify Since we don t want this line click on Remove BS Ed des 2 5 2 Dual Level Optimization Some loads and load effects involve the entire structure for example the hull girder bending shear and torsion of a ship hull These load effects cannot be controlled adequately by a local resizing of a few structural members but rather by the coordinated resizing of all of the members that make up the cross section of the ship In MAESTRO terminology it requires a coordinated resizing of all of the strakes that make up the cross section of the module Likewise many of the more serious types of structural failure are caused principally by these overall load effects For example one of MAESTRO s failure modes for a stiffened panel is Panel Collapse Membrane Yield PCMY Of course in its scope this failure mode relates to occurs in individual panels and for this reason it is checked as part of the strake by strake analysis and adequacy evaluation But if a panel was found to be inadequate it would be inefficient to cure the problem only by a local strengthening of that panel In order to achieve an optimum solution all such panels must be redesigned simultaneously and the optimization must account for the influ
175. efault button on the Overall Defaults page of the Optimization Dialog Box brings up the Group Opt Settings dialog box shown to the left This dialog allows the user to define different Optimization Types for each of the module specific General Groups MAESTRO can optimize based on Weight only Cost only or Multi objective a non dimensional weighted sum of weight and cost The latter is nearly always the true objective in structural design Least weight by itself i e at any cost is appropriate only for aircraft and aerospace vehicles With the multi objective approach the cost implications of weight can be explicitly included for example a weight reduction may mean more cargo capacity and hence more revenue The non dimensional weighted sum is defined as ep ap C 0 0 where C and W are reference values These are simply typical values for the structure In this example they are C 131 7 K DOLLARS and W 15 02 long tons which are nothing 2009 DRS Defense Solutions LLC Advanced Technology Center Tutorials 325 more than the starting values of cost and weight obtained by making an Analysis run before starting the optimization The units were specified in the Units page of the Job Information Dialog Box The resulting non dimensional values are combined by means of weighting parameters P and P which are simply fractions that add to 1 0 In this example for simplicity the values are 0 5 and 0 5 i e
176. efault views that will automatically orient the model for viewing These views can be accessed from the View gt Set View gt menu or by right clicking in the modeling space and selecting from the menu MAESTRO also allows the user to create Named View which can be saved and called up like a default view Body Plan Profile View Plan View Isometric Views Body Plan 2009 DRS Defense Solutions LLC Advanced Technology Center Y hoc be i Profile View 106 MAESTRO 9 0 7 Plan View 2009 DRS Defense Solutions LLC Advanced Technology Center General Isometric Views SouthEast SouthWest NorthEast NorthWest SouthEast 107 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 108 SouthWest 2009 DRS Defense Solutions LLC Advanced Technology Center 109 General HE cH Bp a Fi NorthEast 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 110 Laff aN iS iJ r VY Y Mv NorthWest 2009 DRS Defense Solutions LLC Advanced Technology Center 111 General 4 13 Named Views View Options user defined range and view type plate thickness stress plot eleme
177. efinition extends from one frame to the next can be comprised of two panel elements or three panel elements or any number n The only limitation is that n must divide evenly into the highest section number in the module Note 2009 DRS Defense Solutions LLC Advanced Technology Center 134 MAESTRO 9 0 7 5 2 that section numbering begins with zero Any of the nodes lying in the two end planes of a module can be moved lengthwise out of their plane by any differing amount thus allowing the modeling of complex end shapes and the joining of modules at arbitrary angles or orientations Note that this does not move the end sections or change the end values or section spacing Substructures A substructure is a set of modules which are generally associated with each other e g bow midbody and stern The substructures are merely a convenient means of grouping modules together there are no specific functions or operations associated with substructures A substructure s origin is defined with respect to the global origin and may like modules be oriented in any direction about the X Y and Z axes Module origins and axes are defined relative to their parent substructure s origin and axes For example if the midbody substructure origin is defined as being at X 55m Y Om and Z Om with respect to the global origin then a module within this substructure which starts 75m forward of the global origin or 20m f
178. elect a part in the modeling space to delete This can also be done 2009 DRS Defense Solutions LLC Advanced Technology Center General 59 by right clicking on a part in the parts tree and selecting Delete Mirror gt Model Parts gt Model This option will open the Mirror dialog which is used to mirror the model or add a mirror Parts gt Add Mirror Mirror This menu is used to mirror or add mirror a specific part Once the option is selected from the menu click on the part to mirror or add mirror and follow the prompts in the command tab Materials This option will open the Materials dialog where materials can be created modified and deleted Properties gt Beam Plate Rod Spring Beam This option will open the properties dialog to the beam properties tab Plate This option will open the properties dialog to the plate properties tab Rod This option will open the properties dialog to the rod properties tab Spring This option will open the properties dialog to the spring properties tab 2009 DRS Defense Solutions LLC Advanced Technology Center 60 MAESTRO 9 0 7 ULSAP Parameters This option will open the Ultimate Strength Parameters dialog where sets of parameters can be created modified and deleted M Ultimate Strength Parameters Identification fi v Name defaut Name Type Initial Shape Ratio of Initial Deflection Sti
179. elements This will serve to define all of the properties except for their node locations After creating this prototype select the Quad option from the drop down menu The user can now single click on the first three nodes in the model that are to become the element nodes 1 2 and 3 in the new quad and then double click on the fourth node Repeat this process for as many quad elements as you wish but remember these new quads are based on the properties of the prototype quad 2009 DRS Defense Solutions LLC Advanced Technology Center 176 MAESTRO 9 0 7 After completing the Quick Creation sequence there are two important things to remember The first is to toggle off the quick creation icon and second the Quick Creation process does not update the ID numbers in the dialog box Therefore if you are going to continue using the dialog box you must close the Finite Element Dialog Box and the reopen it Triangle Creation The user must create a prototype triangle element in the usual manner for the other elements This will serve to define all of the properties except for the node locations After creating this prototype triangle select the Triangle option from the drop down menu The user can now single click on the first two nodes in the model that are to become the element nodes 1 and 2 in the new triangle and then double click on the third node Repeat this process for as many triangle elements as you wish bu
180. elements within that select box Once an element is added to the group right clicking on the element will bring up a menu allowing the user to flip normal side or add all elements with the same property material stiffener layout or type This will apply to all elements in the current view part 8 Select a color from the drop down menu to give the general group a unique color 9 Click the Create button The new general group will appear under the group tab of the parts tree under the General folder as the name given in the Groups dialog box Corrosion Group This group option allows the user to define a group that will consider corrosion effects The user can define which side stiffener plate or both the corrosion effects occur Further the user can choose to apply corrosion by a percentage or as a net The user can apply corrosion to the plate web or flange associated with the corrosion group 1 Begin by opening the groups dialog box using the Groups gt Corrosion menu option or from the toolbar Groups Volume Plate Module Section Node Bay General Corrosion B oS St lt lt vhLhlUh Full Strake Full Compound Whole Module Select By Box Module Name MSM Create Delltem Close 2 Click the ID button to assign a unique ID to the corrosion group 3 Type a descriptive name into the Name box 4 Check the Centerline Group if the general group spans the centerline of a half model T
181. en gauge its accuracy from the extent of MAESTRO s changes either an improvement in the measure of merit due to the optimization or the identification and correction of any inadequacies in the starting design or both Oftentimes from experience with a given type of structure it is known beforehand that a particular limit state is likely to be one of the governing constraints in the design For example some ship structural design rules require a certain minimum value of section modulus and for some ship types this requirement is one of the governing constraints In such cases a common technique in rulebased design is to first obtain member sizes that satisfy the local strength rules which are relatively straightforward and then to scale up the design until it just satisfies the overall strength rules such as minimum section modulus of the structure This is about the best that rulebased design can do to do more would require the calculation of the load effects stresses etc and of all of the limit values of the load effects and both of these tasks require a computer One of the aims of this example is to illustrate qualitatively the savings that rationally based design can achieve compared to rule based design Therefore the starting design will be a typical good rulebased design one which just fulfills any governing overall i e module level constraints The relevant constraint is the minimum section modulus requirement the second
182. ence that the redesign has on the overall load effect In other words the requirement constraint that such failure must be cured is part of the module level optimization problem in which the variables are the strake sectional areas At this second level of optimization MAESTRO determines the precise distribution of strake areas that best optimally satisfies the PCMY constraint and all other module level 2009 DRS Defense Solutions LLC Advanced Technology Center Tutorials 333 constraints Consequently for any structure in which the module level load effects combined with other load effects might be sufficient to cause membrane vield of plating dual level optimization should be used This is done by inserting the keyword DUAL as part of the Further Constraints data Alternatively if the input data includes either of the other two module level limit states MIN IMOD and MIN ZMOD then MAESTRO automatically uses dual level optimization To give the designer maximum flexibility the PCMY constraint does not automatically invoke dual level optimization 2 5 3 Nullifying a Structural Limit State The Limit States subpage allows the designer to nullify a structural failure mode which means that MAESTRO will ignore any inadequacy that might occur due to that failure mode and that Limit State will not influence the optimization Obviously this should only be done when the designer is certain that the inadequ
183. ency On Set Transparency Off Show Weight MM UVERRE PPP BABAASE lime e ALPS HULL Le He gt e LVN QD CR x VONEO set current part finemesh general group 001 Select enter a menu or function T command Output Grd Mirror fe Add Mirror Source finemesh general group 001 Target v Flip stiffener side v Reverse Normal m Groups amp Restraints amp Loads Mirror groups Mirror Restraints Mirror loads Concor K Analysis Setup Now that the full model is successfully generated the user can now process the analysis 1 The ALPS HULL analysis model should now be a full model port and starboard Expand the finemesh object again if necessary and right click on the analysis model Choose ALPS HULL from the menu which will launch the Analysis Setup dialog 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 275 Fie Tools View Model Groups Loads Hull Results Help OSHS Beaagsa Gea Geessim Sa ATSA Show Weight i Oo e G finemesh A hiap Set Current Part Fi z 3 su Set View Part g Q m Set Current amp View Part a H Rename z A B Copy L Mirror A Delete A Add Mirror A 2 Set Visibiity On 7 e Set Visibity Off ri Visibility List Pa g Set Transparency On
184. ense Solutions LLC Advanced Technology Center 172 MAESTRO 9 0 7 5 15 Mirroring a Model There are two options when mirroring a part or the full model Mirror and Add Mirror The mirror dialog can be opened by right clicking on a part in the parts tree and selecting Mirror or Add Mirror The dialog can also be launched from the Model gt Mirror gt Parts gt or Model gt Mirror gt Model menu Mirror Mirror C Add Mirror Source Target top fwd sections new part Structure V Do not mirror centerline elements M Flip stiffener side M Reverse Normal Groups amp Restraints amp Loads Mirror groups Mirror Restraints Mirror loads Mirror The mirror function will create a mirror of the selected part s with a new name defined by the user The user also selects the new location or Target of the mirrored part s Add Mirror The add mirror function will create a mirror of the selected part s but includes the mirrored parts in the original part s The location of the new part s is such that the origin is at the same location as the original part but all nodes and elements are reflected through the local X Y plane of the original part 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 173 5 16 Structure Options Do not mirror centerline elements By checking this box MAESTRO will assume all centerline e
185. ense Solutions LLC Advanced Technology Center Analyzing and Post Processing 279 8 10 parameter by selecting Minimum Value Plate Minimum Value Beam or Minimum Value All You can also choose to display only the Positive or only the negative adequacy parameter results Similar to Viewing Stress Ranges Adequacy values can be defined by the user and viewed e g to determine all negative adequacy values The dynamic query icon t v with Adequacy checked from the drop down can be used to highlight an element and recover the adequacy parameters Double clicking the element will echo the results to the Output tab Using Evaluation Patches Toolbar Menu Model gt Evaluation Patch gt Create Evaluate The following tutorial describes what an evaluation patch is and how it is used in MAESTRO What is an evaluation patch A patch is a collection of elements with its boundary supported by bulkheads or beams A patch can also be a single element In traditional MAESTRO a patch is a lengthwise strake panel or a few strake panels if the section per bay is greater than one How do you automatically define patches From the main menu select Model gt Evaluation Patch gt Auto Generate Patches can also be automatically generated when evaluation is selected in an analysis How do you delete all patches From the main menu select Model gt Evaluation Patch gt Delete All How do you manually create a p
186. ent and the deflection of the plating flange Mode Mode Il and Mode III The following sign convention for theoretical computation is used Stress Positive if compressive Bending moment Positive when the plating is in compression Lateral Deflection Positive towards the stiffeners Eccentricity Positive towards the stiffeners 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 259 Negative Bending Moment Deflection amp negative here The three modes of failure are Mode Stiffener induced collapse due to compression failure of the stiffener Collapse occurs due to compression failure of the stiffener flange The combination of in plane compression and negative bending is illustrated in the figure below Collapse occurs when the stress in the mid thickness of the flange o My 6 AG A y 5 OSat PL 1 equals the failure value which is the minimum of yield stress oy or the elastic tripping stress o r The terms in the above equation are A and Cross sectional area and moment of inertia of the beam column M and 6 Bending moment and deflection due to lateral load dead load A Eccentricity y distance from the centroidal axis of the c s to the mid thickness of the stiffener flange Mode II Plate induced collapse due to compression failure of the plating This failure mode occurs due to a combi
187. er 102 MAESTRO 9 0 7 This icon will hide the elements outside of the defined range for the current plot E This icon will toggle shrink elements on or off This icon enables dynamic rotation of the model After selecting this toolbar button use the left mouse button to rotate the model Use a left down click to rotate the model and release the mouse button to set the new view angle The command equivalent of this item is Set View Angles NOTE The user also has the choice of using the wheel button if available to invoke the dynamic rotation functionality Simply move the mouse while simultaneously holding the wheel button down This icon rotates the model about the global X axis each time it is clicked This icon rotates the model about the global Z axis each time it is clicked This icon rotates the model about the global Y axis each time it is clicked This icon will toggle the direction of any sign sensitive command Rotations will occur in a positive direction and zoom command will magnify views when the is enabled and conversely rotations will be in a negative sense and zooming will zoom out when the is enabled NOTE Icons only flip rotate the model in constant increments of 15 degrees To rotate the model to a specific angle execute View gt Set View gt Specify from the menu The user is then prompted to supply the angle of rotation as an argument in the Command Line Specific angles can
188. er Geometry Finite Element Modeling 157 5 11 Longitudinal This option allows the user to create a construction line in space through a specified point in the longitudinal i e module s local X dir direction Transverse This option allows the user to create a construction line in space through a specified point in the transverse i e module s local Z dir direction Vertical This option allows the user to create a construction line in space through a specified point in the vertical i e module s local Y dir direction Delete Construction Geometry All This option will delete all existing construction geometry CMarkers This option will delete all existing construction markers CLines This option will delete all existing construction lines Specify This option allows the user to select which construction geometry to delete using the mouse Creating Strakes Toolbar Menu Model gt Elements gt Create Modify gt Strake Keyboard lt Ctrl k gt Strakes are a convenient way of creating all of the structural elements between two sets of end points The strake data is defined in the MAESTRO Strakes dialog box via the General Plating Frames Girders Stiffeners and Deletions tabs This tutorial shows the procedure for creating a strake between a set of defined end points 2009 DRS Defense Solutions LLC Advanced Technology Center 158 MAESTRO 9 0 7 1 Begin by
189. er must first change to the Element Type view toggle the Dynamic Query icon move the mouse cursor over a particular element right click the mouse and finally select the menu item To return to viewing all elements you must select View gt Wetted Elements to uncheck the option By ID Material Beam Property Plate Property Rod Property Stiffener Layout This option allows the user to view the model by material ID plate property ID beam property ID rod property ID or stiffener layout ID The dynamic query function can be used to highlight an element and change the beam rod or stiffener layout property by right clicking on the element in the corresponding view 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 PlateProp ID Cm got ln om AOL CA HH A HT 7 LL HHH Groups Corrosion Side User defined Color Volume Plate Pressure Side Corrosion Side This option allows the user to view the side of the element which corrosion is applied to shown as pink if a corrosion group is defined User defined Color This option will display the currently viewed groups as the user defined color set in the groups dialog 2009 DRS Defense Solutions LLC Advanced Technology Center General 43 Volume Plate Pressure Side As mentioned above MAESTRO distinguishes between a positive and negative pressure face by a pink and gray f
190. ers Point This command allows the user to create a construction marker at a specified location in space either interactively with the mouse or through the command line Bisect This command allows the user to create a construction marker at a specified fraction along a particular line segment To enter a specified fraction delete the in the command line and type the fraction in decimal form i e 0 25 Project This command allows the user to create a construction marker at the projection of a specified point on an indicated line Cross This command allows the user to create a construction marker at the crossing of two indicated lines If the two lines or their extensions do not physically intersect in space the marker is placed at the closest point on the primary line the first line selected to the secondary line the second line selected The two lines are selected using the mouse Mix This command is similar to bisect but instead the user selects two points of a line segment Construction Lines 2 Points This option will create a construction line in space between two selected points Parallel This option will create a construction line in space passing through a specified point and parallel to the specified direction vector The direction vector is often specified by using the mouse to select another line segment in the model parallel to the desired vector 2009 DRS Defense Solutions LLC Advanced Technology Cent
191. erse Positive Thickness 0 m 2nd Flange Create Modify Delete Close 2 Make sure the appropriate module is set as the current part and click the ID button to assign a unique ID to the element 3 Click in the Node 1 box and click the two nodes that make up the beam element in the model 4 Select the beam property from the drop down menu If the property is not defined click 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 163 the Property button to create a new beam element property 5 Check the By Associated Element box if the beam is associated with another element such as a strake quad or triangle and choose the element type and choose the Element ID from the drop down menu 6 Choose the Web Orientation from the drop down menu and specify Node 3 if applicable 7 Enter values in the 2nd Flange Thickness and Width fields in order to simulate an l beam by way of using a T beam property plus a second flange Please see the Second Flange verification section for examples 8 Click Create This procedure can be repeated to create additional beam elements Toolbar Menu Model gt Elements gt Create Modify gt Rod This tutorial shows the procedure for creating an individual beam element 1 Begin by opening the Finite Element Rod dialog using the Model gt Elements gt Create Modify gt Rod menu the toolbar or clicking the Rod t
192. es box to do one more cycle However if we did use the same Modeler file then the previous output file ex2_no_girder OUT would be overwritten and the page numbering would change We don t want that because this tutorial has referred to some of those pages Therefore we will make a new Modeler file and then enter the data for cycle 6 as follows 1 Go to the Main Menu click on File Save As and enter ex2_cycle6 as the file name Click on Save 2 Since the job title is printed at the top of each page we should also change it to ex2_cycle6 Go to the Job Information Dialog Box and in the Job Title box replace ex2_no_girder by ex2_cycle6 3 In that same Job Information Dialog go to the Restart Cycle box and click the up arrow twice to change 3 to 5 The go to the Design Cycles box and change 2 to 1 to do just one more cycle 4 Click on OK 5 Bring up the Optimization Dialog Box Model Optimization click on Group Opt Settings In that Dialog Box the ID will be 1 and the Group will be STANDARD 6 In the Discretization section select On 7 Let s say that plating is available in 1 16 inch increments Therefore in the Plate Thickness Increment box enter 0 0625 8 Click on Modify 9 Steps 6 8 were for the STANDARD Group Click the ID down arrow and select general group 1 Then repeat steps 6 8 10 Save this new Modeler file go to the Main Menu and click on File Save 11
193. esign Inc MAESTRO This software is protected by U S and Intemational copyright laws Welcome to MAESTRO 9 0 7 a comprehensive program that leverages the power of Finite Element Analysis for the naval architect MAESTRO is a finite element tool providing powerful structural design and analysis capabilities for naval architects A robust application backed up by first class support MAESTRO has been designed and created by a group of naval architects that care about your experience with the software Simply put we feel successful when our software can leverage your design talents to create better vessels If you have questions that can t be answered through this Help or the forum feel free to contact us at maestrosupport orca3d com We enjoy hearing about your projects your application of MAESTRO and your challenges and will do our best to help 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 Latest Updates Latest Updates 9 2 1 Latest Updates Updates and changes to MAESTRO will be described here listed by release number You can also read the Release Notes which are included as part of the installation to see a complete history of the releases and changes to MAESTRO Version 9 0 7 MAESTRO Release Notes MAESTRO is a finite element analysis program for rationally based analysis evaluation and structural optimization of ships offshore structures and o
194. ewly created file will contain the section locations and wetted cross sectional areas as well as coordinates for the points defining the cross section based on the defined wetted elements in the model Wetted Surface This option will launch the Export Wetted Surface dialog which allows the user to select the location to save the wet file The newly created file will contain the node locations and elements for the elements defined as wetted in the model Directional Stress Results gt Stress gt Results gt Stress gt Define Results gt Stress gt Show Directional Direction Direction Introduction Method for Determining In plane Stress Vector Global X Global Y Global Z User defined Cutting Plane 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 301 Introduction When constructing a finite element model it is ideal to generate elements such that their respective local X and Y axes are all aligned in a uniform direction i e aligned to a global axis The reason for this is so the analyst can be assured the direction of the stress vectors are uniform when recovering stress in a given axis e g post processing Mid X Normal stress The presentation of stress in a uniform manner such as this allows the analyst to better assess the stress path in a given direction Because it is impossible to construct a complete full ship model in this manner MAESTRO prov
195. factors for various load cases Local buckling implies buckling of plating between stiffeners When failure occurs due to buckling of plating crosswise to the stiffeners e g buckling due to lengthwise compression in a transversely stiffened panel then such buckling is collapse of the panel rather than unserviceability Therefore this limit state uses the word failure represented by the letter F in the acronym PFLB rather than the letter C or S o denotes a stress that acts lengthwise parallel to the stiffeners and o will denote a stress that acts transversely across the stiffeners The corresponding failure stresses elastic or inelastic buckling stress or for thick plating yield stress when the applied stresses act in isolation are denoted o p and oyp Similarly the value of shear stress that would cause failure again elastic or inelastic buckling or yield when it alone acts on the plating is denoted tp The values of oqp and t are calculated from the equations of chapter 12 of 1 The corresponding strength ratios are R 6 6 R1 6 o and Rg t t These act alone strength ratios are then converted to 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 265 8 9 1 2 interactive values R and R by an extension of the procedure given on page 435 of Reference 1 To give a brief picture of this for a slender plate the shape of the
196. ff Context Default Color Context UserDef Color Free Edges Rename Copy Delete Wet UnWet Flip Normal Eval Un Eval Do Undo Master Create Patch Refine Modify Set View Part This will set the highlighted group as the current view Set Visibility On This will toggle the visibility on for the highlighted group Set Visibility Off This will toggle the visibility off for the highlighted group Normal This will display the highlighted group with the normal side of elements colored Volume Pressure This will display a graphical representation of the volume pressure for the selected group if defined in the currently selected load case Context Default Color 2009 DRS Defense Solutions LLC Advanced Technology Center 200 MAESTRO 9 0 7 This will display the highlighted group with the default MAESTRO element colors Context UserDef Color This will display the highlighted group with the user defined colors selected in the Groups dialog Free Edges This will check the highlighted group for free edges Rename This will allow the group to be renamed within the groups tree Copy This will create a copy of the highlighted group Delete This will delete the highlighted group Volume This will report the volume of the group if applicable Volume Table This will produce a table of tank volumes and masses based on the currently selected load case The following menu options are
197. ffener Spacing Ratio of Initial Deflection Stiffener Length Ratio of AL Breadth Heat Affected Zone Thickness Shape Length in Width in Type Peak Pressure lbf in 2 Time s Dent Diameter in Dent Depth in Crack Length in Corrosion Depth in Pitting Intensity Create Modify Delete Close Nodes gt Create Modify gt Delete gt Renumber IDs Create Modify gt This menu option is used to create or modify endpoints or additional nodes by opening the appropriate dialog box Delete gt 2009 DRS Defense Solutions LLC Advanced Technology Center General 61 This menu option is used to delete endpoints and additional nodes Note a module must be set as the current part in order to use this functionality Once endpoint or additional node is selected the user will be prompted to specify the ID of the endpoint or additional node to delete Selecting unused nodes will delete any endpoints or additional nodes not being used to define an element Renumber IDs This option is used to renumber the node ID of the current modules endpoints and additional nodes This will eliminate any gaps in ID numbers if nodes are deleted Elements gt Create Modify gt Delete Create Modify gt Beam Bracket Quad Rod RSpiine Spring Triangle Compound Strake This menu is used to create or modify an additional element compound or stra
198. for a nodal or elemental FE Tag Deletions Filters Fixed a bug so that the filters in the deletions dialog work as expected Saving Loading Results Fixed a bug so results consistently save and load with a mdl file e ULSAP Results Fixed a bug so that ULSAP results are automatically saved and loaded with a mdl file e ULSAP Adequacy Parameters Fixed a bug so only ULSAP Adequacy parameters are shown in an ULSAP analysis Graphical Bugs Fixed 2009 DRS Defense Solutions LLC Advanced Technology Center 12 MAESTRO 9 0 7 Show This Thickness Only Fixed a bug that allows user to switch back to all thicknesses using the dynamic query once the Show this thickness only option is selected Corner Stress Fixed a bug so now the check box for Corner Stress changes the stress contour plot between nodal and elemental contour plots Compound Element Effectiveness Fixed a bug so now non transverse compound elements can be defined as longitudinally effective using the dynamic query Bending Moment when Switching Load Cases Fixed a bug so the hull bending moment plot updates when different load cases are selected Load Case Selection Fixed a bug to make sure queried loads are consistent with the load case from the load case selection drop down menu Pressure Plots when Switching Load Cases Fixed a bug so the color plot and legend updates each time a different load case is selected from the load case drop down
199. formation Scale Range Tools amp View Style Corner Stress Off Viewports Video Driver Options des ALPS HULL Off Single Hardware 2 buffer Shrink Elements Split Vertical M Construction Geometry C Split Horizontal Advanced V Cutting Planes C Four Views World Axes F No Contour Plat x eu 5 Click OK when finished Individual element stresses for the defined range are now presented Elements that are outside of the user defined range are colored grey 6 To hide the elements outside of the user defined stress range click the icon Failure Mode Evaluation Introduction A large and complex thin wall structure can fail in many different ways which are called the failure modes The various factors that determine the failure modes include the geometry of the structure the boundary conditions and the loading on the structure MAESTRO provides two different types of failure mode evaluations for stiffened panels and their components MAESTRO and ALPS ULSAP MAESTRO also provides ALPS HULL which addresses progressive collapse of the hull girder Click on the link for either method for more detailed information on how to perform and interpret each type of evaluation 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 255 Adequacy Parameter For a structure to be safe under a given load condition the load effect Q must remain below the limit
200. function and the cost have increased from 0 748 to 0 766 about 2 4 whereas the weight has stayed essentially the same The reason for this is that most of the weight is in the plating which stayed the same thickness whereas the number of stiffeners increased which increased the welding cost and hence also the objective 2 17 Active Constraints in the Final Design After deleting the girders in strakes 1 and 4 these strakes have 10 design variables Since MAESTRO uses an improved version of linear programming to perform the optimization the number of active constraints is always equal to the number of design variables For the Final Design these constraints are listed in the table on page 26 of the output There is one minimum constraint and four proportionality constraints For min max and proportionality constraints it is possible to show graphically how these constraints govern the final scantlings and Figure 2 c illustrates this The other five constraints are three failure modes and two Area constraints The latter are minimum values of the strake cross sectional area to satisfy the overall hull girder constraints MIN IMOD and MIN ZMOD From the nature of the failure modes it is possible to make a logical connection between the design variables and the constraints that most influenced them as shown in the following table Design Variables Governing Constraints BFF TFF BSF TSF HSW TSW 20
201. g Composite Layer Stresses section for details This procedure can be repeated to create additional plate element properties This tutorial shows the procedure for creating a new beam property 1 Click the Beam tab 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 147 Properties Plate Beam Rod Spring Identification Name default v ID oo001 v Type Tee Height Width Thickness in Web Height in Web Thk in Down Create Delete Modify Close 2 Click the ID button to assign a unique ID to the beam element property 3 Give the beam element property a descriptive name 4 Select the beam type from the drop down menu 5 Define the Web and Flange if applicable Height Width and thickness 6 Select the material 7 Click Create Note the beam properties list can become expansive and it may be helpful to sort the beam properties in the dialog box and this order will be maintained when selecting a frame girder or beam property This tutorial shows the procedure for creating a new rod element property 1 Click the Rod tab 2009 DRS Defense Solutions LLC Advanced Technology Center 148 MAESTRO 9 0 7 Properties Plate Beam Rod Spring Identification Name Scantling Input Method Principal Dimensions Properties amp Material Outside Diameter fo in Wall Thickness fo in Ma
202. gle of planing bottom at transom Angle of the tangent slope of the planing bottom at the transom For a temporary solution the tangent slope of the planing bottom at a point BTR 4 off the centerline located at the aft most point of LPRC is recommended BM midship breadth on waterline Molded breadth on the waterline located at MIDP BPX maximum breadth over chines Maximum breadth of the outside of the chine excluding external spray strips BTR breadth of the chine at the transom Breadth of the outside of the chine excluding external spray strips at the transom aftmost point of LPRC 2009 DRS Defense Solutions LLC Advanced Technology Center Appendices 401 BX maximum breadth on waterline Maximum breadth of the waterplane DISV displacement volume Immersed volume of the hull neglecting appendages Large added volumes such as skegs may have a contribution to hull volume and there should be data agreement between SWH and DISV ENTA half angle of entrance Angle of waterline at the bow with reference to centerplane neglecting local shape at stem For a temporary solution the tangent slope of the waterplane at a point BX 10 off the centerline is recommended LOS overall submerged length Entire length of the submerged portion of the vessel including items such as bulbs that extend beyond the limits of LWL LPP length between perpendiculars Reference length that define
203. goal 3 01 NOTES 1 Revision 3 01 includes a new sectional AREA entity at the request of the US Navy and other users 2 All data tags items preceded with must exist in the header in the order and format given 3 Following the UNITS data tag must be a line that reads either SI or User Defined 4 The HYDRO entity has been reduced to a subset of the ITTC computer symbols called the Interim Standard Transfer Set STS The list of supported terms is included in the description of the HYDRO entity At their own risk programs may output other ITTC values however these are not strictly supported and may or may not be read by other programs 5 It is suggested that IDF interfaces be tested by trading files with other programmers who have IDF interfaces Please contact the IMSA Technical coordinator above to arrange this 3 02 NOTES 2009 DRS Defense Solutions LLC Advanced Technology Center 390 MAESTRO 9 0 7 1 The General Form showed COORDINATE SYSTEM preceeding COMMENTS while the specific entity defintions had these reversed The specific entity definitions have been revised to be the same as the General Form 3 03 NOTES 1 Added the PROPSECTS entity for describing propeller geometry GENERAL FORM IDF 3 01 or greater SENTITY entity type VESSEL NAME identifier for this vessel DATA SOURCE name of program that wrote the file DATE date TIME time SUNITS units COORDINA
204. gth of the transverse and longitudinal edges of the local plate panels between stiffeners due to the combination of the plate bending stress transverse in plane stress longitudinal in plane stress AVSIGX and shear stress TAU is predicted by use of the distortion energy criterion The Von Mises stress is given by E 2 2 2 On PT PO 0 0 3 The strength ratios for PSPBT L are then given by 2009 DRS Defense Solutions LLC Advanced Technology Center 264 MAESTRO 9 0 7 y 50 vm RPsPBT Oy and y 50 vm RPsPBL Oy where Omt Von Mises stress at the midlength of the transverse edge Gym Von Mises stress at the midlength of the longitudinal edge Ys load factor for serviceability Panel Failure Local Buckling PFLB In previous versions the input data for MAESTRO evaluation component such as panel pressure stresses plate thickness and stiffener scantlings are the average quantities over the corresponding patch Since Evaluating PFLB Panel Failure Local Buckling does not require to use the width of the grillage or patch it is more appropriate to evaluate these failure modes at the element level rather than the patch level which is now the behavior for this limit state PFLB refers to the failure related to the buckling elastic or inelastic of plating between stiffeners Buckling may be caused by o 6 or t or by various combinations of these Appendix A lists out the buckling
205. gy Center Analyzing and Post Processing 237 8 4 Natural Frequency Analysis A natural frequency analysis can be performed by MAESTRO by checking the option in the Loads dialog A separate load case should be created for the natural frequency analysis LoadCase 002 v Name fest v General Mass Point Force Pressure Balance Load Safety Factor 1 0 Current Status From Other Menus Structure amp Loads S e Options on Masses amp Accelerations Cul oads Symmetry Include structure s mass Self Weight Has Scaled Module Mass M Include gravity Has Immersion 7 Floating Structure Ship etc 10 Dry Inverse lter 1000 Draft 107 83in Additional acceleration End Moment Corrosion User defined CG Delete Modify Close Help In the Current Status from Other Menus window on the General tab gives a summary of the natural frequency analysis criteria To change the criteria click the Criteria button next to the Natural freq analysis line Clicking this button will launch the Natural Frequency Analysis Setup dialog 2009 DRS Defense Solutions LLC Advanced Technology Center 238 MAESTRO 9 0 7 Natural Frequency Analysis Setup Job Type C WetMode Dry Mode Natural Frequency Method Range of Interest Subspace From Hz Inverse power C Lanczos To Hz M Sturm Check Number of natural frequencies to be computed Eigenvalue tolerance Shift in Hz
206. h along non stiffened edge Minimum of segments between stiffeners Convert beam frame girder web to Convert beam frame girder s flange to C ALPS HULL Nastran Map O default m 1 Quad v Beam X Cancel 4 Use the default settings and click OK You should now be to the same point as FineMeshStep2 mdl In a top down analysis the original coarse mesh elements are not deleted from the model To view the coarse and fine mesh elements together select View gt All Modules from the menu 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 289 In order to solve the fine mesh model you must first solve the coarse mesh model and then solve the fine mesh model separately This can be done by solving the coarse mesh model as usual and then right clicking on the fine mesh model in the parts tree and selecting solve A box can also be checked to Solve All Fine Mesh Models in the Analysis Evaluation dialog box This option will first solve the coarse mesh model and then the fine mesh model with one command RSplines are used to transmit the displacements of the coarse mesh nodes to the fine mesh nodes along the RSpline element Embedded Analysis The embedded fine mesh analysis is a one step analysis The coarse mesh model and the fine mesh model are tightly connected by the Rspline elements When the embedded model is created by the refine method the Master element
207. han any previous evaluation The precise level of detail is specified in the Job Information data In this example the output is on pages 49 to 67 Note that the stress values and other results on these pages are superseded by designerspecified alterations to the structure to be described in Section 2 13 The output for the additional members is on pages 68 70 and the output for the module evaluation is on page 71 2 13 Review of the Design Besides monitoring the cost and the adequacy of the design it is important to examine its principal features what are the main changes and what constraints are directing the design Figure 2 compares the initial design and the current design defined on page 47 of the output and Figure 2 b shows some of the active constraints Instead of four stiffeners there are now only two 1 7 at this stage it is still too early to discretize and the plating is thicker 2 13 1 Sample Investigation Of An Active Constraint This section shows briefly how to obtain information about the active constraints taking the FYCF2 constraint as an example The active constraints are given on page 45 For strake 1 one of the active constraints arising from a limit state or failure mode is FYCF2 which means Frame Yield Compression Flange the R prefix simply means it was active repeatedly For a frame failure mode the number at the end is always 1 2 or 3 signifying the worst location strake edge 1 strake edge 2 or th
208. has to be deleted Otherwise the structure is over stiffened by the fine mesh model An embedded fine mesh model has no Master element The RSpline element provides a constraint stiffness matrix and the stiffness matrix is added into the global stiffness matrix so the coarse mesh model and the fine mesh model can be solved together at the cost of larger band width and much more computer time For top down analysis the global result never changes no matter how the fine mesh model is modified but for Embedded fine mesh analysis the global results are dependent on the fine mesh model and they are closely coupled The following example will walk through creating a simple embedded fine mesh model 2009 DRS Defense Solutions LLC Advanced Technology Center 290 MAESTRO 9 0 7 1 Begin by opening FineMeshStep0 mdl from the Models and Samples MAESTRO Installation directory 2 Create a general group of the middle 4 strake panels including the strake frames Groups Volume Plate Module Section Node Bay General Corrosion 007 Name General Group 001 7 Centerline Group J Full Strake Full Compound Whole Module I Select By Box Module Name ID Jtop ex1 sub1 mod1 strake Quad 9 3 Jtop ex1 sub1 mod1 strake Quad 8 3 top ex1 sub1 mod1 strake Quad 8 2 Jtop ex1 sub1 mod1 strake Quad 9 2 top ex1 sub1 mod strake Frame 9 2 J top ex1 sub1 modi strake Frame 8 2 RES create
209. he About MAESTRO dialog providing the currently installed version of MAESTRO and copyright information About MAESTRO MAESTRO Version 9 0 0 Copyright 2009 This computer program is protected by copyright law and international treaties Unauthorized reproduction or distribution of this program or any portion of it may result in severe civil and criminal penalties and will be prosecuted to the maximum extent possible under the law Toolbars The MAESTRO interface contains five toolbars to allow the user to access often used commands with a single mouse click These include the Standard toolbar the Pre Processing toolbar the View toolbar the Post Processing toolbar and the Refine Element toolbar All commands associated with toolbar buttons can also be accessed via the main menu Please see the GUI Interface figure to see the toolbar layout 2009 DRS Defense Solutions LLC Advanced Technology Center General 99 Standard Toolbar Pre Processing Toolbar Viewing Toolbar Post Processing Toolbar Refine Element Toolbar Standard Toolbar The Standard toolbar which is located at the upper left part of the interface just below the main menu provides a fast and easy means of performing some common tasks Most of the icons on the toolbar correspond to a specific file menu command A brief description of the action performed by each toolbar icon is given below D This icon creates a new modeler file
210. he MAESTRO installation directory under the Models and Samples folder 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 310 ICE API Global X via XY Cutting Plane Global X via XZ Cutting Plane Wary A YZ Cutting Plane via Y Global via XY Cutting Plane Y 3 YZ Cutting Plane Global Z via tting Plane Global Z via XZ Cu Demonstration of the 6 User Defined In Plane Stress Vector Orientations Figure 13 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 Advanced 312 MAESTRO 9 0 7 9 1 Advanced The following topics discuss advance capabilities offered with MAESTRO These include batch processing accessing results via a COM interface and importing 3rd party hydrodynamic loads Batch Processing Introduction MAESTRO has the ability to perform batch processing This is useful for example when the user would like to sequentially solve multiple models with many load cases without having to manually launch the process Further several post processing keywords are available for users to compare a result to a known value The batch file will consist of at least three tokens separated by a space first to launch behind the scene MAESTRO second to identify the model and third to define a keyword Note the second and third tokens may need to be bracketed by quotation marks if there
211. he Optimization radio button in the Job Type section must be selected which unlocks options in the lower half of the Dialog Box The above figure shows that the user has told MAESTRO go through 3 design cycles The checked Final Evaluation box tells it to perform an analysis of the final design cycle scantlings and to put the results into the ex2 OUT file The checked Save Scantlings box instructs MAESTRO to create a restart file that records the scantling values at each design cycle for each module that is being optimized Restart files are explained in a later section 2 2 Optimization Dialog Box Page 1 Optimization Data And Overall Defaults In MAESTRO the optimization is performed separately for each module The optimization data is specified in two Groups 1 one Standard Group a module independent group of Min Max constraints and other Constraint Sets which serve as default Constraint Sets for all modules 2 any number of module specific General Groups containing Constraint Sets which can selectively override the default Constraint Sets and which can also include other types 2009 DRS Defense Solutions LLC Advanced Technology Center Tutorials of Constraint Sets that are not in the Standard Group 323 These two Groups and their component Constraint Sets are defined in the Optimization Dialog Box pictured below There is no toolbar icon for this Dialog you obtain it from the Main Menu by cli
212. he direction of the beam s Y axis which is determined by the web orientation This convention means that when the beam is attached to plating as in a strake or on a compound the pressure is positive when it acts on the smooth side of the plating i e the side opposite the additional beam For example on a transverse bulkhead if the additional beam faces forward then a positive pressure would be applied to the aft side of the bulkhead causing a forward force If an additional beam is a substitute for a strake based transverse frame element then it will automatically receive the strake related loads If this is not desired then the frame element should be deleted Delete Geom amp Load explicitly using the Deletion tab found in the Strake dialog An additional beam will always receive whatever loads are defined for it here in this data group The Pressure on Node 1 and Pressure on Node 2 columns define the pressure load value at the corresponding nodes The Width column defines the width of the pressure load For vertical beams on the centerline of the overall structure a half width should be used Edge 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 223 LoadCase Name General Mass PointForce Pressure Balance Plate LinPress Plate Surface Head Plate Surface Zero AdditionalBeam Edge Module Name Type ID Stress N mm 2 Edge Side Modify De
213. he radius of gyration about the user defined center of rotation Once selected a dialog will launch prompting the user to input the center of rotation 2009 DRS Defense Solutions LLC Advanced Technology Center 36 MAESTRO 9 0 7 Calculate Radii of CG Center of Rotation x 924 837 in Ye 116 622 in Cancel z 0 0392808 in After the center of rotation is defined click OK The results will be displayed in a new dialog box as well as be echoed to the Output tab MAESTRO 8 9 8 Radi of Gyration in xGyr 164 062 yGyr 530 291 zGyr 522 742 About X 924 837 Y 116 622 Z 0 0392808 Find FE Tag This option will launch the Find FE Tag to locate a node or element by it s FETag Find FeTag Nodal C Element FeTag cancel Click the radio button to choose between Nodal and Element and type the FeTag to search A dialog will list the node or element location for the enter FeTag This location will be echoed to the Output tab 2009 DRS Defense Solutions LLC Advanced Technology Center General 37 4 4 MAESTRO 9 0 0 A Element top s2 midbody m1 fr 25 49 Strake 20 Sec 17 has FeTag 2313 Renumber FE Tag This option will renumber all Nodal and Element FE Tags in the model to remove any gaps in FE Tag numbers Edit Nastran Data This option allows the user to open and edit the Nastran nas file if applicable in the MAESTRO Output tab or a separa
214. he sample models are fiber stack O N45 P45 0 original mdl fiber stack O0 N45 P45 0 mdl and fiber stack P45 0 90 P45 mal Options This option will launch the View Options dialog Refresh This option will allow the user to refresh the graphics 2009 DRS Defense Solutions LLC Advanced Technology Center 58 MAESTRO 9 0 7 4 5 Model Menu The Model menu provides options to build constrain and balance the model A brief description of each option is discussed below Parts Mirror Materials Properties gt ULSAP Parameters Nodes gt Elements gt Stiffener Layout Evaluation Patch d Define Constraints Balance Summary Parts gt Create Modify Combine Copy Delete Create Modify This option will open the Parts dialog where a structure or module can be created or modified This is the same as clicking the parts icon di Combine This option will move the selected module beneath the substructure that is set as the current part The module is selecting by clicking on it with the mouse in the modeling space Note a substructure must be set as the current part for this option to be allowed since a module cannot be added beneath another module Copy This option will create a copy of the selected part and allow the user to name and set the location of the new part The part is selected by clicking on it in the modeling space Delete This option is used to s
215. hickness m Orientation D Failure Theory Shear Bondin Up Down Create Delete Modity Close This tutorial shows the procedure for creating a new plate element property 1 Click the Plate tab 2 Click the ID button to assign a unique ID to the plate element property 3 Give the plate element property a descriptive name 4 Right click in the first large white space of the dialog and click Add This will add a layer to the new property 2009 DRS Defense Solutions LLC Advanced Technology Center 146 MAESTRO 9 0 7 Properties Plate Beam Rod Spring Identification Name defaut v m 00001 v Laminate Failure Criteria Failure EE Allowable Interlaminar Shear Stress Ibffin 2 Remove Layer sus al Thickness in Orientation D J Thickness in Failure Theory Shear Bondin Up Down Create Delete Modify Close 5 Select the material for the layer from the drop down menu Define a thickness in the units shown 6 Click Create Composite Structures MAESTRO can create composite structures for strake quad and tri shell elements In order to create a composite structure follow the steps for a plate property definition but now additional layers can be added and fiber orientations set for each layer Input the appropriate Laminate Failure Critera for the composite structure Stresses can be recovered for each layer of a composite material See the Recoverin
216. his will automatically combine the mirrored group into one single group if the model is mirrored 5 Checking the Full Strake Full Compound box will include the entire strake or compound 2009 DRS Defense Solutions LLC Advanced Technology Center 196 MAESTRO 9 0 7 as the part of the general group by clicking on any part of it 6 Checking the Whole Module box will include all elements of the module by clicking any part of it 7 Click inside the main white part of the dialog box and then select the elements that make up the tank boundary faces The Select By Box option can be checked to use a box window to add all the plate elements within that select box Once an element is added to the group right clicking on the element will bring up a menu allowing the user to flip normal side or add all elements with the same property material stiffener layout or type This will apply to all elements in the current view part If the Whole Module box is checked when selecting elements an additional dialog box will open Corrosion Corrosion Side Stiffene Corrosion Method fe NetRemaining C Corroded NetCorroded This allows the user to define the corrosion side and method for defining the corrosion This will be applied to all elements in the selected module 8 Select a color from the drop down menu to give the corrosion group a unique color 9 Click the Create button The new corrosion group wil
217. his will produce a text box with data for the highlighted section of the distribution Further the user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph entity of interest 2009 DRS Defense Solutions LLC Advanced Technology Center General 71 View Self Weight View Gross Weight View Buoyancy View Net Force View Longitudinal View Horizontal gt View Transverse gt Weight Summary View Self Weight View Gross Weight View Buoyancy View Net Force View Longitudinal gt View Horizontal gt View Transverse gt Weight Summary View Self Weight The View Self Weight command under the the Hull menu is used to display the MAESTRO calculated modeled weight The term modeled weight refers to the weight calculated by MAESTRO based on the materials and elements that make up the FE model As shown below MAESTRO produces a display of this weight distribution Further MAESTRO echoes this distribution to the Output window which is found at the bottom of the MAESTRO GUI In conjunction with the View Self Weight command the user can use the Dynamic Query tool which can be initiated via the t v icon to query the distribution graph To use this functionality the user must select the View Self Weight command toggle the Dynamic Query icon and move the mouse cursor over a particular portion of the graph This will produce a text box with graph
218. hould be interpreted as weight MAESTRO will automatically convert these weights to mass internally by dividing by gravity 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 209 NOTE In a half model all specified values of mass should be half values For a half model all masses except for Bay Set are assumed to be symmetric and there is no need to define the corresponding mass in the un modeled half For example a plate group defined in the modeled side will be assumed to be included in the un modeled side as the same mass weight Each method for defining a mass is described in more detail below Volume Module Section Node Plate Bay Volume Mass The Volume mass tab is for the user to add tanks or volume groups to the current load case definition These previously defined volume groups are made available to the user via the drop down menu After a volume group is added the user can specify the parameters of the volume contents LoadCase Name General End Moments Acceleration Mass Point Force Pressure Balance Corrosion Volume Module Section Node Plate Bay x Add Total Mass CK OverFill Volume Name Type Value Density kg m 3 Pipe Head m Y Centerline m Z Horiz Surface m gt Modity Del Row Close Help 2009 DRS Defense Solutions LLC Advanced Technology Center 210 MAESTRO 9 0 7
219. ical Bending Moment Finite Element Results Not Recommended for Large Model Node Element Displacement Stresses amp Adequacy Parameters Text File This option will open a dialog allowing the user to save a text file of the elements materials and results Contour This option toggles on the stress contour view A check mark will appear next to the option in the menu when contour plot is turned on 4 10 Help Menu The Help menu provides several resources to the user for help with MAESTRO A brief description of each option is discussed below MAESTRO Help FAQ Forum Release Notes Technical Support About MAESTRO Help This option will launch the MAESTRO help file This can also be done by clicking the MAESTRO Help icon 2009 DRS Defense Solutions LLC Advanced Technology Center 98 MAESTRO 9 0 7 4 11 FAQ This option will launch the MAESTRO website FAQ section These FAQ are the same as the ones found in the MAESTRO help file Forum This option will launch the MAESTRO forum where MAESTRO users and technical support personnel post tips tricks and technical support questions and responses Release Notes This option will open the MAESTRO release notes providing a summary of new features and fixed bugs Technical Support This option will launch your desktop email program with an email pre addressed to support maestro com About This option will open t
220. ich is 80 of yield p s f 1 25 For that reason the FYCF2 adequacy parameter is exactly zero page 52 2 13 2 Individual Influence of the Active Constraints The first eight active constraints page 45 two minimum and six proportionality are all explicit functions of the design variables and so they can be shown directly on Figure 2 b as the governing dimensions of those design variables The constraints relating to structural failure do not have any such explicit relationship but it is clear from the nature of each of them that FYCF2 would mainly control the frame web height and PSPBL and AREA would mainly control the number and height of the stiffeners and the plate thickness The R in front of PSPBL FYCF2 and AREA indicates that the constraint was repeated i e was a strong influence 2 14 Example Of Design Modification Deletion Of Girders Inspection of Figure 2 b reveals an interesting fact the girder is as small as it can possibly be The girder web is as small as it can be 10 higher than the frame web and a thickness that is 1 50 of the height and the flange is at minimum breadth the 9 inches required for flexuraltorsional buckling and minimum thickness limited by the 1 25 proportion Also none of the girder limit states was an active constraint and all of the girder adequacy parameters are well above zero page 52 for strake 1 It therefore appears that the girders may not be needed This possib
221. ick the two nodes that make up the spring element in the 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 165 model 4 Select the spring property from the drop down menu If the property is not defined click the Property button to create a new spring element property 5 Click Create This procedure can be repeated to create additional spring elements RE Menu Model gt Elements gt Create Modify gt RSpline This tutorial shows the procedure for creating an rigid spline element RSpline 1 Begin by opening the Finite Element RSpline dialog using the Model gt Elements gt Create Modify gt RSpline menu the toolbar or clicking the RSpline tab in the Finite Elements dialog box Finite Elements Spring Rod Beam Triangle Quad RSpline Bracket MultiPoint Constraints Available on COM Solver Master Nodes e RSpline Node 1 Node 2 Top Down Auto RBE2 RBE3 Slave Nodes Create Modify Delete Close 2 Make sure the appropriate module is set as the current part and click the ID button to assign a unique ID to the element 3 Select the type of RSpline element For a description of the three types please see the Model Organization section 4 Click in the Node box and click the node that makes up the first part of the rigid spline element in the model 2009 DRS Defense Solutions LLC Advanced Technology Ce
222. ides the option to display all panel elements stress in a given global direction regardless of the elements local orientation When this option is checked on all panel elements in plane stress vector will be aligned to the global X global Y global Z or a user specified direction The dialog for defining directional stress is shown below Before describing the options available for defining directional stress it is useful for the analyst to understand the internal logic used by MAESTRO to determine the re aligned in plane stress vector The following example shows how in plane stress vectors are determined and aligned to the Global X axis The user has the ability to also align the in plane stress vectors to the Global Y and Global Z axes in a similar manner Define Stress Direction FullModel Current View Part Align Panel Inplane Stress Vector to Global x fe via X2Z XY Cutting Plane C via XZ Cutting Plane C via XY Cutting Plane Global Y C via xy Z Cutting Plane C via XY Cutting Plane C via YZ Cutting Plane Global Z C via X2 Y2 Cutting Plane C via XZ Cutting Plane C via YZ Cutting Plane User Defined Cutting Plane C Specify In plane Vectors Fi Method for Determining In plane Stress Vector 2009 DRS Defense Solutions LLC Advanced Technology Center 302 MAESTRO 9 0 7 For panel elements neither of whose local x and y axes are in the Global direction selec
223. ies of the prototype spring After completing the Quick Creation sequence there are two important things to remember The first is to toggle off the quick creation icon and second the Quick Creation process does not update the ID numbers in the dialog box Therefore if you are going to continue using the dialog box you must close the Finite Element Dialog Box and the reopen it Compound The compound quick create functionality works similar to the other quick create options The Compounds menu option is a toggle on or off and will show a check mark when it is on To use the compound quick create you must first create a compound Once the compound is created you can toggle on the compound quick create option from the ae icon Next create a prototype element in the compound and then follow the procedure for creating additional elements of that type after selecting the type from the quick create menu After completing the Quick Creation sequence there are two important things to remember The first is to toggle off the quick creation icon and compound option and second the Quick Creation process does not update the ID numbers in the dialog box Therefore if you are going to continue using the dialog box you must close the Compound Dialog Box and the reopen it 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 Checking The Model Checking The Model 179 6 1 Checking The Model Th
224. ility of the highlighted part to On Set Visibility Off This will toggle the visibility of the highlighted part to Off If a substructure s visibility is set to off all of the modules within that substructure will have their visibility set to off Visibility List This will launch the Visibility List dialog which looks the same as the parts tree but allows the user to toggle the visibility on off with one click for each module or substructure Set Transparency On This will set the highlighted module or substructure as transparent Set Transparency Off This will set the highlighted module or substructure as not transparent Show Weight This will show a dialog providing the weight of the highlighted module of substructure If a substructure is selected the weight will be for all of the modules within that substructure combined Defining Materials amp Properties Quick Reference Defining Materials Creating a Plate Property Creating a Beam Property Creating a Rod Property Creating a Spring Property 2009 DRS Defense Solutions LLC Advanced Technology Center 144 MAESTRO 9 0 7 Menu Model gt Materials The materials defined in the dialog box are global and are used as reference for element properties and therefore should be defined prior to creating an element property This tutorial shows the procedure for creating a new material 1 Begin by opening the Materials dialog box from the
225. ility was investigated by deleting the girders However it is important to note that any change in the number of strakes or the number of girders requires that the optimization job be performed again from the beginning cycle number 1 in order that the restart file has the correct number of strakes and girders The job can be repeated for the same number of design cycles or if the convergence had been slow or rapid for more or fewer cycles Another important consideration is that up to now all of the text of this document refers to the output of the original job EX2 OUT and so we certainly do not want to overwrite that file Therefore we will now create a new Modeler mdl file by copying and modifying the model in the following steps 1 Create a new model by going to the Main Menu clicking on File Save As entering ex2_no_girder as the file name and clicking on Save 2009 DRS Defense Solutions LLC Advanced Technology Center 344 MAESTRO 9 0 7 2 Delete the girders by going to the Strake Dialog Box and for strakes 1 and 4 uncheck the Enable Girders check box and click on Modify 3 To avoid confusion between the outputs of the original model and the no girders model it will be helpful to change the job title to ex2_no_girder because the title is printed at the top of each page Go to the Job Information Dialog Box and replace the existing title by ex2_no_girder 4 MAESTRO Job Inf
226. ill be created Help Models and Samples and System Help Directory The Help directory contains the electronic manual in both Compiled HTML Help File chm and Adobe Acrobat pdf formats Supporting manuals i e MAESTRO Basic Features Tutorial Legacy Data Prep Manual and MAESTRO Release Notes are also included in this directory Models and Samples Directory The Models and Samples directory contains a variety of MAESTRO example models verification models sample programs C C and other data to assist the user in learning and understanding MAESTRO All of the data found in this directory is appropriately referenced throughout the documentation System Directory The System directory contains all of the necessary files that allow MAESTRO to function properly These files should not be removed or modified The System directory also includes support files and documentation for the Sentinel security device in the event troubleshooting is required 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 Geometry Finite Element Modeling 128 MAESTRO 9 0 7 5 1 Geometry Finite Element Modeling The topics in this section provide detailed information on the MAESTRO functionality used during the Finite Element Modeling stage of an analysis Model Organization Elements Strakes and Modules Substructures In the design of large structures it is usually advisable to divide the
227. in four tables which in this example are on pages 2124 of the MAESTRO output As mentioned elsewhere before commencing any MAESTRO DESIGN job an ANALYSIS job should always be performed first because it does several data checking operations that are not done in a DESIGN job because of the cyclic nature of the latter This example presupposes such an ANALYSIS job which among other things would have established the adequacy of all of the strakes As indicated in these four tables all of the constraints are satisfied On page 21 it can be seen that one of the most important of them Panel Collapse Stiffener Flexure is well satisfied having an adequacy parameter of 0 194 This means that its ratio of strength load or capability demand is above the minimum required value of 1 5 if it was right at 1 5 then the adequacy parameter would be exactly 0 This again shows that the starting design is already as good or better than a typical rulebased design Such design does not calculate the ultimate strength of each panel because this would require a computer even with the simplest algorithm the algorithm used by MAESTRO for panel strength is given in Section 14 2 of Ship Structural Design However through a combination of theory and accumulated experience with a given type of structure rules can be developed such that the design variables which they prescribe do give an ultimate strength that is close to the target value Page 24 gives the
228. ing is accounted for by the panel element The neutral axis location and the moment of inertia of each hybrid beam are automatically calculated and printed In a finite element model a beam element is nothing more than a line element joining two nodes and setting up a relationship between their displacements and rotations For this reason most finite element programs display a beam element simply as a line In that case they do not look like real beams and they can be difficult to see especially in a large model In order to make the 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 131 beam elements more visible and more realistic MAESTRO displays them as web panels that is it displays the web of the beam but not the flange CTRIR Triangle Element This is a flat constant strain element that can be placed between any three nodes ina module CRod The rod element is a pin jointed bar which can connect any two nodes in a module The rod element can carry axial force and axial torsion only Compound This consists of any user defined assemblage of in plane membrane elements bar beam triangle and quadrilateral elements in any transverse section of any module CELAS2 Spring Element The spring element is a linearly elastic spring which can connect any two nodes in a module These elements can carry either force or moment loads Forces in the spring element will
229. ings 2 19 Updating the Modeler file by Importing the DAT File Finally it is necessary to update the Modeler file in this case ex2 mdl because if MAESTRO was run again and was allowed to write a new DAT file the above updates would be lost To update the Modeler file go to the Main Menu click on File Import and select the newly updated DAT file Since the new scantlings are not in the Properties lists the Modeler will create new properties for all of them NOTE At the time of writing July 2005 the Modeler s Import option has not been extended to include the optimization data It will be extended in a future update 2009 DRS Defense Solutions LLC Advanced Technology Center Tutorials 351 10 2 3 References and Figures References and Figures 1 Hughes O F Ship Structural Design Society of Naval Architects and Marine Engineers Jersey City NJ 1988 2009 DRS Defense Solutions LLC Advanced Technology Center 352 MAESTRO 9 0 7 Girders Deleted Discretize Variables Objective Functi 0 75 pe Cos 4 5 6 ke 12 T T T T T 1 0 1 2 3 4 5 6 Cycle Figure 1 History of Objective Function Cost and Weight 2009 DRS Defense Solutions LLC Advanced Technology Center Tutorials 353 2009 DRS Defense Solutions LLC Advanced Technology Center 354 MAESTRO 9 0 7
230. integer equation become SLAIN k 1 N E l b Sars but NE ag ey Yok lly a VG ids j 1 2 3 N Gy NES k 1 2 3 j i 5 Whereas this is a finite number of equations only in a finite number of points this boundary k condition can be satisfied After i are determined the velocity potential can be obtained by i 1 2 3 N k 5 kif Gk x d 5 DEL Xi Yi Zi 61 6 ds k 123 6 The each panel added mass can be gotten by k k k i 1 2 3 N mi n iA k 123 The added mass of the body is N m gt mk i l 3 Application Half Sphere with free surface 2009 DRS Defense Solutions LLC Advanced Technology Center 372 MAESTRO 9 0 7 X4 Fig 1 The half sphere can be expressed by panels above Fig 1 The Landweber value of the 1 in p r Cai ror added mass are 3 for heave and 3 for surge and sway The P and r are the density of water and the radius of sphere respectively The numeric results are shown in the Table 1 Panel MAESTRO NX Nastran V5 0 Model File e y e e e ae EE EN EE EE LS CT ol 1099 588 6 591 6 1068 Sphere1458 md l Table 1 P 1025 kg m3 1 00 100 586 6 586 6 1073 4 622 82 646 76 1144 6 1611 6 631 7 1054 5 Sphere100 mdl 5 9 2 1458 References 1 Sarpkaya T Isaacson M Mechanics of Wave Forces on Offshore Structures Van Nostrand Reinhold New York 1981 2 L Landweber and Matilde Macagno Added Mass of a Rigid Prolate Spheroid Oscilla
231. ite element types most commonly used in MAESTRO are described below 2009 DRS Defense Solutions LLC Advanced Technology Center 130 MAESTRO 9 0 7 COMPOUND een TRANSVERSE STRAKE FRAME red ADDITIONAL BEAM ELEMENT orange QUAD ELEMENT light blue TRIANGLE ELEMENT light green ROD STRAKE brown GIRDER yellow z ellen STRAKE PANEL dark blue Figure 2 MAESTRO Elements CQuadR Stiffened Panel This is the most general and hence most useful panel element in MAESTRO and it is the default element for all panels strakes and quads It is an orthotropic shell quadrilateral that automatically includes the bending stiffness if the stiffeners in either the longitudinal or the transverse direction It is the same element as in the NASTRAN program but in MAESTRO the quite large task of calculating the orthotropic properties is automated The CQuadR element is a 4 noded flat shell element with each node having 6 degrees of freedom Hybrid CBAR Beam Element This element has been developed for modeling of beams frames girders additional beams attached to plating The plating acts as one of the flanges of the beam and MAESTRO takes this into account in calculating the beam s flexural properties using a user specified effective breadth of this plate flange In contrast the axial stiffness is for the beam only which is why element is called hybrid because the in plane stiffness of the plat
232. ke and will open the appropriate dialog Delete gt Select Al Visible gt Select This option will open the Deletions dialog All Visible gt 2009 DRS Defense Solutions LLC Advanced Technology Center 62 MAESTRO 9 0 7 Beams Bracket Compounds Quads Rods RSplines Springs Strakes Triangles This option allows the user to delete all visible elements of a specific type by choosing the desired element from the menu Stiffener Layout This option will open the Stiffener Layout dialog where stiffener layouts can be created modified and deleted Evaluation Patch gt Auto Generate Create Evaluate Delete All Auto Generate This option will automatically create evaluation patches from the model s elements Create Evaluate This option will launch the Evaluation Patch dialog Delete All This option will delete all evaluation patches defined for the model Define Constraints This option opens the Constraints dialog Balance This option opens the Balance dialog Summary This options opens the Model Summary dialog providing the total number of nodes and elements as well as the total modeled length width and height 2009 DRS Defense Solutions LLC Advanced Technology Center General 63 Model Summary Number of Nodes 3018 Number of Elements 11607 Total Length 1980 in Total Width 434 254 in Total Height 444 in corel 4 6 Groups Menu
233. l Location Sections Default Values Origin Location Rotation Angles x i in X axis 0 deg y J0 in Y axis 0 deg z in Z axis 0 deg Create Modify Delete Close 5 The Sections and Default Values tabs only apply to modules and thus are ignored for substructures Additional substructures can be created in this same manner Now we are ready to create a module within our newly created substructure 6 Click to the General tab and select the substructure from the local parts tree on the right Substructures and Modules General Location Sections Default Values Part Type C Module Substructure PartName _ top s1 Create Modity Delete Close Note the Part Name box now lists the substructure name after top 7 After the substructure name type a forward slash and a descriptive name for the module 8 Click the radio button for Module and then click Create Note clicking the next to the substructure name will now display the modules that make up that substructure 9 After making sure the new module is highlighted in the local parts tree and the name shows up in the Part Name box select the Location tab The Part Name box and Parts tree specify which part is currently active and can be modified 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 139 Substructures and Modules General Location Sections Default Values
234. l Row Close Help This pressure load option serves to impose a uniform in plate stress at the lower or upper end of a strake panel in the lengthwise direction i e parallel to the X axis of the panel or the mean plane panel if the strake is warped and or skewed At each end the stress applied there is positive if it acts in the positive X direction and negative if it acts in the negative X direction Thus to impose a lengthwise compression on the panels of a strake the stress applied at the lower end smaller section number would be positive and the stress applied at the upper end would be negative The intention is that the panel end coincides with a cut cross section of the model and the stress comes from an adjacent portion of structure that is not being modeled For greater flexibility in modeling the stresses can be applied at any section along the strake they are not limited to the reference and opposite ends of the strake The program automatically converts the stress into equivalent nodal forces in the panel X direction and equivalent nodal moments about axis parallel to the panel Z axis If the strake is warped and or skewed the axes are those of the mean plane panel These forces and moments are then transformed to structure coordinates and applied to the model The Edge Side column defines the end lengthwise of the strake that will receive the specified stress Lower represents the edge that corresponds to the smaller section n
235. l appear under the group tab of the parts tree under the Corrosion folder as the name given in the Groups dialog box Wetted Group A general group of all defined wetted plate elements can be created using the Groups gt Wetted Elements menu This will automatically create the general group wet and does not involve using the Groups dialog Elements are defined as wetted by checking the box for quads and triangles or by selecting side or bottom as the ocation in the strakes dialog 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 197 7 2 Groups Tree The groups tree displays each group which has been created in the model in a folder format directory Each group appears as its own directory and cannot be a subdirectory of another group 2009 DRS Defense Solutions LLC Advanced Technology Center 198 MAESTRO 9 0 7 Workspace groups general node main engine plate deck winch volume fr 65 73 outboard fr15 21 outboard 25 33 outboard 33 41 outboard 41 49 outboard fr5 15 outboard fr65 73 centerline Th fi Parts ME Groups Any group can be copied deleted or renamed in the group window using the popup menu launched by right clicking the mouse 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 199 Set View Part Set Visibility On Set Visibility O
236. l you will also want to display the output file ex2 out and that is achieved from within the Modeler by going to the Main Menu and clicking File gt Analysis Evaluation gt Legacy Version of MAESTRO gt View Output File If you do not have this file or if it becomes corrupted you can generate a new copy by running the ex2 job simply by clicking on the execute button at the right end of the upper toolbar 1 2 Description Of The Structural Model This example demonstrates optimization of a simple but realistic module a rectangular box girder with vertical and transverse symmetry both of structure and of loading The structure might for example be a segment of a pontoon in a semi submersible The one module model of the structure is shown in the following figure If you open the Modeler file ex2 mdl 2009 DRS Defense Solutions LLC Advanced Technology Center 320 MAESTRO 9 0 7 you will have a color picture of the structure You may wish to shrink and move the Modeler display so that you can see it side by side with this document As in the earlier tutorial you can gain more display space by closing the Parts Tree window and hiding the Refine toolbar under Tools gt Toolbars in the Main Menu The model consists of four strakes To simplify the example the maximum design value of transverse pressure 1s the same for all strakes This means that the module has vertical symmetry about the half height of l
237. lane in a similar manner to the above example which was for the Global X direction Global Z via XZ Cutting Plane This will align the elements in plane stress vector to the global Z direction based on the intersection of the XZ cutting plane and the element in a similar manner to the above example which was for the Global X direction Global Z via YZ Cutting Plane This will align the elements in plane stress vector to the global Z direction based on the intersection of the YZ cutting plane and the element in a similar manner to the above example which was for the Global X direction User Defined Cutting Plane This will allow the user to define the direction of two arbitrary vectors Vector 1 and Vector 2 which determine a special cutting plane to which the in plane stress vector will be aligned The options for setting the stress vector are shown in the Define Stress Direction dialog which can be opened from Results gt Stress gt Define Direction 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 307 Define Stress Direction FullModel Current View Part Align Panel Inplane Stress Vector to Global x via XZ XY Cutting Plane via XZ Cutting Plane C via XY Cutting Plane Global Y C via x lt Y Y2 Cutting Plane C via XY Cutting Plane C via YZ Cutting Plane Global Z C via XZ YZ Cutting Plane C via xz Cutting Plane C via YZ Cut
238. lane as described above Global X via XZ Cutting Plane This will align the elements in plane stress vector to the global X direction based on the intersection of the XZ cutting plane and the element as described above Global X via XY Cutting Plane This will align the elements in plane stress vector to the global X direction based on the intersection of the YZ cutting plane and the element as described above Global Y Global Y via XY YZ Cutting Plane This will align the elements in plane stress vector to the global Y direction based on largest projected area on the XY or YZ plane in a similar manner to the above example which was for the Global X direction Global Y via XY Cutting Plane This will align the elements in plane stress vector to the global Y direction based on the intersection of the XY cutting plane in a similar manner to the above example which was for the Global X direction Global Y via YZ Cutting Plane This will align the elements in plane stress vector to the global Y direction based on the intersection of the XZ cutting plane and the element in a similar manner to the above example which was for the Global X direction Global Z 2009 DRS Defense Solutions LLC Advanced Technology Center 306 MAESTRO 9 0 7 Global Z via XZ YZ Cutting Plane This will align the elements in plane stress vector to the global Z direction based on largest projected area on the XZ or YZ p
239. lane bending the errors are 2 3 and 1 6 respectively For the twist the theoretical value is 0 0233 radians and not 0 0321 as given in 2 and MAESTRO matches this value exactly Table 1 presents the results Figure 1 Straight Cantilever Beam Length 6 0 Height 0 2 Depth 0 1 E 1 0e v 0 3 mesh 6 x 1 MAESTROJ Theoretical Relative MSC Solver Error Nastran V3 0 In Plane Clamped Unit force trapz mdl Shear in Y _ B o trapz1 dat v 0 1068 v 0 1081 1 20 rapz1 mod free end trapz1 f06 Clamped Unit force trapz mdl atone end inZ hw 0 4252lw 0 4321 1 62 fw 0 4264 fapz2 dat rapz2 mod free end trapz2 f06 2009 DRS Defense Solutions LLC Advanced Technology Center 362 MAESTRO 9 0 7 11 1 3 Clamped Unit trapz mdl at one end twisting _ _ 0 trapz3 dat of beam moment at _ 7 x rapz3 mod free end 0 00233 0 00233 00306 trapz3 f06 Table 1 Cantilever Beam Results Curved Beam The third test is the curved beam problem The geometry dimensions material properties and loading conditions are shown in Figure 1 The element shape in this test is not exactly rectangular and so this test includes the effect of a small irregularity in the element Table 1 presents the results of this test which shows that the MAESTRO QUAD4 element has about the same accuracy as the MSC QUAD4 element y Z Figure 1 Curved Beam Inner Radius 4 12 Outer Radius 4 12
240. le the required value is 15000 ins The actual value is 1 209x106 72 16 792 and so as mentioned earlier the starting design satisfies this constraint almost exactly with an adequacy parameter that is close to zero 056 on page 25 This shows that as desired the starting design is reasonably efficient Because of the symmetry the value is the same for both deck and bottom 2 10 3 Module Optimization Page 26 of the output gives the results of the first cycle of module optimization under the heading Values at start of module opt n cycle 2 Because the initial design had slightly more than the required section modulus the strake areas have been decreased slightly The program performs two cycles of module optimization The program obtains the new values of TPL HSW TSW BSF and TSF by scaling the old values so as to match the new strake area The scaling is applied only to these five variables the other nine variables remain the same including those that could have contributed to the strake area increase the number of stiffeners STF and the girder variables They are never changed at the module level because their strongest influence is on the strakebased limit states The program then recalculates the adequacy parameters using the new panel scantlings and using the same load effects as before the finite element analysis is done only once in each overall cycle 2 10 4 Strake Optimization At this point the program performs
241. lement will now report the chosen layer stress 2009 DRS Defense Solutions LLC Advanced Technology Center 286 MAESTRO 9 0 7 2 87E 003 2 71E 003 2 04E 003 1 87E 003 1 71E 003 1 54E 003 Be Thickness 0 8 in 1 37E 003 FeTag 31 Layers 4 TopFiber2LocX 0 00 Deg 1 21E 003 Layer 2 Stresses Ibf in 2 SigX 3 8380E 003 1 04E 003 Tyz 2 8596E 001 8 72E 002 Strains X 8 4026E 004 Y 1 4576E 003 7 06E 002 XY 2 3174E 003 39E 002 3 72E 002 2 05E 002 The model used in this sample Composite_4Layer mdl can be found in the Models and Samples MAESTRO installation folder for reference 8 13 Creating and Analyzing a Fine Mesh Model The following tutorial shows the process to creating and analyzing a fine mesh model There are four different types of fine mesh analysis models that can be automatically created in MAESTRO a top down model an embedded model a ALPS HULL model and a Nastran Map model Top Down Analysis The top down analysis is a two steps analysis The coarse mesh model has to be solved first The boundary displacements of the fine mesh model are calculated using coarse mesh results via linear interpolation The displacements of the coarse mesh nodes are then applied to the fine mesh nodes through RSpline elements The fine mesh model is a different finite element model with imposed displacement boundary conditions This method uses the same logic as MG DSA
242. lements were modeled with their full properties and thus not create a copy Flip Stiffener Side By checking this box MAESTRO will flip the stiffener side of the mirrored elements such that the stiffener orientation matches with the original part s Reverse Normal By checking this box MAESTRO will reverse the normal direction of the mirrored elements such that the element normal side is preserved in the original part s Groups amp Restraints amp Loads Options Mirror Groups By checking this box any groups created in the original part s will be mirrored in the new part s Groups tagged as centerline groups will automatically combine the two groups into a single group Mirror Restraints By checking this box any restraints not on the centerline will be mirrored and applied to the new part s Mirror Loads By checking this box any defined loads will be mirrored and applied to the new part s Quick Create BE The Quick Element Creation icon a is composed of a toggle button and a drop down button 2009 DRS Defense Solutions LLC Advanced Technology Center 174 MAESTRO 9 0 7 EndPt AddNode Strake Quad Tri Beam Rod spring Compound This capability is a powerful tool used during the modeling building phase in the FEA process Toggling this command On the user can create endpoints nodes strakes quads triangles beams rods springs and compounds without the use of dialog boxes Th
243. lete CGeom gt 2 Hold the mouse over CLine and the construction line options will fly out from the menu Repeat CMarker 2 Points Parallel Delete Cceom Longitudinal Transverse Vertical 3 Select one of the options to create a construction line 4 Follow the instructions in the command tab at the bottom of the screen to define the construction line 5 Repeat this process to create an additional construction line that intersects the first one 6 Access the construction geometry menu and hold the mouse over CMarker and the construction marker options will fly out from the menu Repeat Pont CLine r Bisect Project Delete CGeom Cross Mix 7 Select the Cross option 8 Click on one of the construction lines near the intersection point Then click on the second construction line A construction marker will appear at the intersection This point can be used to snap EndPoints or additional nodes to The Repeat command can be used to create multiple construction lines or markers by selecting the construction geometry to create and then clicking on repeat in the menu 2009 DRS Defense Solutions LLC Advanced Technology Center 156 MAESTRO 9 0 7 Construction geometry can be deleted by holding the mouse over the Delete CGeom option and the delete options will fly out from the menu Repeat CMarker gt CLine gt Delete CGeom gt All CMarkers CLines Specify Construction Mark
244. lings for the girder have been selected from the above paper The results obtained from MAESTRO have been found to be in good agreement with the experimental results given in the paper Girder Collapse Compression Flange Plate GCCF GCCP Girders are loaded as a beam column and girder collapse may occur due to combined 2009 DRS Defense Solutions LLC Advanced Technology Center 266 MAESTRO 9 0 7 8 9 1 3 bending and buckling Allowance is made for the frames which partly restrain the girder and influence its mode of buckling Collapse is assumed to occur when there is compressive yielding in either the girder flange or plate flange as there is very little reserve strength beyond this point for beam columns The stresses in the girder flange and plate flange are investigated at each frame and strength ratios are calculated for the two constraints If P be the maximum axial load that the girder can withstand then it can be shown by the beam column approach that Pur Mo Px o A A Z o P Detailed theory can be obtained from section 11 3 of Ref 1 Oy Girder Failure Modes Serviceability Serviceability limit states are defined when the deterioration or loss of other less vital functions have occurred Girder Yield Compression Tension Flange Plate GYCF GYCP GYTF GYTP Compressive failure of a girder is in general a complex buckling phenomenon and to serve as an approximate
245. lity Plate Bending Transverse and Longitudinal PSPBT and PSPBL In previous versions the input data for MAESTRO evaluation component such as panel pressure stresses plate thickness and stiffener scantlings are the average quantities over the corresponding patch Since Evaluating PSPB Panel Serviceability Plate Bending does not require to use the width of the grillage or patch it is more appropriate to evaluate these failure modes at the element level rather than the patch level which is now the behavior for this limit state The limit states PSPBT and PSPBL Panel Serviceability Plate Bending Transverse and Longitudinal deal with plate bending due to pressure and do not consider or allow for any permanent set they require that the total stress at the plate surface membrane stress bending stress remains below yield by the specified safety factor Since pressure can vary with every section of a strake these limit states are evaluated for every section along the length of each strake The bending stress in a plate due to lateral pressure is given by the expression 2 a ie where k is a constant that depends on the boundary conditions and the aspect ratio of the plate Values of k are given in Figure 9 6 of Ref 1 This bending stress is automatically calculated by MAESTRO based on the evaluation patch parameters and incorporated into the Von Mises stress calculation described below Surface yield of plating at the mid len
246. luding one two or four viewports The number in the upper right corner of each viewport indicates the ID of that viewport and the current view part is displayed in the window border of each 2009 DRS Defense Solutions LLC Advanced Technology Center 26 MAESTRO 9 0 7 viewport The active viewport s window border is highlighted in dark blue The user can control how and what is seen in the main display through the commands in the View menu Commands to rotate the current view can also be accessed with a single mouse click via the Viewing toolbar Several more commonly used viewing commands can be accessed by clicking the right mouse button anywhere in the main display area This results in a pop up menu being displayed from which the user can perform operations such as zooming in or out fitting the view panning the view toggling to the previous view setting any of the five standard views and toggling perspective projection on and off Single View 2009 DRS Defense Solutions LLC Advanced Technology Center LT Lill wom 28 MAESTRO 9 0 7 SR SRE HUN RE CE ie FE GEE NN a GNT TELE LA ATT ui TUNER Split Horizontal View 2009 DRS Defense Solutions LLC Advanced Technology Center General 29 ie is B BA TT Ih 22201 Un 4 Views 4 2 File Menu The File menu provides several com
247. lutions LLC Advanced Technology Center 246 MAESTRO 9 0 7 8 6 Analysis Results The dynamic query icon LM can be used to highlight a stiffened panel and recover the stresses in the plate Double clicking the element will echo the results to the Output tab The Stiffener Flange Axial stress will always be displayed as SigX regardless of the stiffener orientation because it is reporting the stiffener local X or axial stress strake 18 Quad Sec 17 Thickness 0 5 in Stf Layout 5x3x5 16 1 0 FeTag 2353 Stresses Mid Ibf in 2 SigX 3 8127E 003 SigY 3 7584E 002 Tau 2 2883E 002 SigVM 3 6609E 003 Stresses Top Ibf in 2 SigX 4 2806E 002 SigY 3 8127E 003 Tau 2 2883E 002 SigVM 3 6394E 003 Stiffener Flange Axial SigX 1 9227E 002 As with the bare plate elements the dynamic query drop down can be used to filter which location stresses should be displayed Note there is no bottom stresses reported for a stiffened panel only the Stiffener Flange Axial stress went Rests 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 247 The following tutorials shows the basic functionality for viewing the stress and deformation results 1 Click on the Result menu to open the drop down menu Deformed Model Stress Adequacy List b Export Output gt Contour 2 Click on Deform to show the model in a def
248. lysis Setup Load Setup Plate Initial Condition C Hogging Sagging Max Deflection Thickness 0 Number of Incremental Loading Steps Residual Stress Yield Stress 0 Bending Stiffener Initial Condition Vertical Rotation Increment Max Deflection Length 0 Horizontal Rotation Increment Residual Stress Yield Stress 9 Shear Force amp Torsional Moment Aluminum Heat Affected Zone Vertical Shear Force Breadth Horizontal Shear Force Yield Stress Ratio Torsional Moment Cancel Post processing The user can review the following results from the progressive collapse analysis at a given Step e SigXX Stress to Yield Stress Ratio e VonMises Stress to Yield Stress Ratio e The particular Failure Mode which are summarized in the table below Failure Mode Acronym Failure Mode Description OC Overall Collapse PB Collapse of plating between support members stiffeners BCC Beam column Type Collapse SWB Local Buckling of Stiffener Web TR Flexural torsional Buckling of Stiffener GY Gross Yielding 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 277 RT Rupture due to Tension CC Crushing due to Compression e SigXX SigYY SigXY SigVM The user can graphically plot these various values by right clicking in the GUI which will launch the menu shown below Once the menu appears the user first chooses the result parameter of interest followed by the Step of interest The co
249. mdl can be found in the Models and Sample directory Introduction Ship hulls are subjected to a variety of hull girder or local load components Of these vertical bending is a primary hull girder load component It is known that the horizontal bending may sometimes be large in the magnitude approaching the magnitude of vertical bending moment when the ship runs at an oblique heading in waves Also in some vessels such as bulk carriers carrying dense cargo such as iron ore an uneven alternate hold loading condition is normally applied and as a result large shearing forces will be imposed Moreover torsion is normally considered to be important for vessels with low torsional rigidity due to large deck opening such as for instance in container vessels and some large bulk carriers 2009 DRS Defense Solutions LLC Advanced Technology Center 270 MAESTRO 9 0 7 Figure 1 Hull girder sectional load components Local plate elements of ship structures are subjected to lateral pressure loads due to cargo or water To view a complete picture of hull girder ultimate strength behavior therefore all hull girder sectional load components mentioned above i e vertical bending horizontal bending vertical sectional shear horizontal sectional shear and torsion in addition to local lateral pressure loads see Fig 1 should be considered simultaneously in a consistent procedure for hull girder ultimate strength analysis
250. menu Deformed Model Changes Fixed a bug that prevented model from being undeformed if structure was changed in the deformed mode Contour Stress Plot Fixed a bug so that the stress legend updates correctly between load cases when viewing a contoured stress plot Hide Elements Outside Range Fixed a bug that now has Hide Elements Outside Range icon functionally properly This option will now hide elements that are not within the range of displayed values Stiffeners on Wetted Elements View Fixed a bug so that when stiffeners are turned on they remain in view on the wetted elements when selecting View gt Wetted Elements Mirrored Wetted Elements Fixed a bug so the wetted faces of wetted elements in a mirrored module or substructure are shown correct graphically Adequacy User Defined Range Plot Fixed a bug so results update correctly when switching between load cases 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 Introduction 14 MAESTRO 9 0 7 3 1 3 1 1 Introduction The topics in this section provide some basic information about MAESTRO what it is for and what you can do with it About MAESTRO MAESTRO is a design tool specifically tailored to suit naval architects and their finite element analysis and limit state failure mode evaluation needs The objective of any structural finite element analysis is to accurately determine the response of a structural s
251. mes and girders but for simplicity we here use the same values for both 2 3 Constraints Imposed Directly On Design Variables In addition to the inbuilt constraints relating to structural failure and other limit states MAESTRO allows the designer to specify any number of other constraints directly on the design variables These constraints arise from many factors such as avoidance of local failures production and fabrication considerations and operational requirements There are three types of such constraints A those involving only one design variable and which specify a minimum and or a maximum value for it or a fixed value for it B those involving a pair of design variables and which impose a linear relationship equality or inequality between them C those which freeze any number of design variables to the values that have already been assigned to them in the finite element data NOTE It is mandatory that all design variables either be assigned a fixed value be frozen or have minimum and maximum values specified for them The default minimum maximum constraints are always specified in the first page Overall Defaults of the Dialog Box and they constitute Constraint Set 1 of the optimization data The proportionality constraints are defined in the second page of the Dialog Box In this example 2009 DRS Defense Solutions LLC Advanced Technology Center 328 MAESTRO 9 0 7 they are all
252. mit states in which the structure or member has failed in its primary load carrying role and the serviceability limit states which involve the deterioration or loss of other less vital functions Typically the first letter is P G F or B referring to panel girder frame or beam The second letter indicates the type of failure it may be either C collapse or S serviceability or it may indicate a particular type of unserviceability Y yield or B buckling MAESTRO Adequacy Parameters All Load Cases Minimum Value Plate PCSF Collapse Stiffener Flexure PCCB Collapse Combined Buckling PCMY Collapse Membrane Yield PCSB Collapse Stiffener Buckling PYTF Yield Tension in Flange PYTP Yield Tension in Plate PYCF Yield Compression in Flange PYCP Yield Compression in Plate PSPBT Serviceabilty Plate Bending Tran PSPBL Serviceability Plate Bending Long PFLB Failure Local Buckling Mimimum Value Beam GCT Tripping GCCF Collapse Compression in Flange GCCP Collapse Compression in Plate G F YCF Yield Compression in Flange G F YCP Yield Compression in Plate G F YTF Yield Tension in Flange G F YTP Yield Tension in Plate FCPH Collapse Plastic Hinge Minimum Value All Negative Positive MAESTRO ALPS ULSAP Adequacy Parameters All Load Cases Minimum Value Plate PCPM Plate induced failure at Midspan PCCB Overall Grilage Collapse PCPE Plate ind
253. model AutoSave A new auto save feature has been added to MAESTRO The user can select the number of executed command s in between auto saves from File gt AutoSave Frequency Recover Model A new feature has been added under File gt Recover which automatically recovers a model after an unexpected closing of MAESTRO Documentation The documentation has been completely overhauled with a focus more on how to Additionally all of the documentation is now in a single location which can be found via the Help menu or help icon Sentinel Security Drivers Servers The Sentinel System Driver both for USB and Sentinel Protection Server for Network locks are now integrated into the MAESTRO installation process Therefore there is no need for the user to install security drivers servers separately The integrated installation checks to determine the necessity of installing the Sentinel Driver Sentinel Protection Server Help Menu The new Help menu now includes links to the website forum support email and FAQ FAQ Updated FAQ section in the help file and on the website Null Beam and Stiffener Properties There are now predefined null beam and stiffener layouts when creating a new model This eliminates the need to define these for an unstiffened panel or unframed strake Set Current amp View Part There is now an icon and a right click menu option in the parts tree to set the current and view part for a module or substructure a
254. mon functions within MAESTRO A brief description of each option is discussed below 2009 DRS Defense Solutions LLC Advanced Technology Center 30 MAESTRO 9 0 7 New Ctrl N Open Ctrl O Save Ctri s Save AS Import d Export gt Analysis Evaluation gt Job Information Preferences Units Capture View gt Print Ctri P Print Setup 1 Final Model mdl 2 HighSpeedFerry mdl 3 HighSpeedFerryFullModel mdl 4 OSV10 mdl 5 test mdl 6 C Program Files ferry mdl Autosave Frequency Recover Model Exit New This option will open and new MAESTRO file Open This option allows the user to select and open a previously saved MAESTRO mdl file Save This option will save the current MAESTRO model file Save As This option will allow the user to choose the location and save the current MAESTRO model file under a new file name Import gt This option will open a fly out menu of file types for MAESTRO to import 2009 DRS Defense Solutions LLC Advanced Technology Center General 31 DXF GHS IDF MAESTRO dat MAESTRO mdl Nastran Ship Motion Export gt This option will open a fly out menu of file types for MAESTRO to export Ansys Nastran Wetted Cross Section Wetted Surface Analysis Evaluation This option will open a fly out menu of different analyses types Global FEA Local FEA Limit State Evaluation Post FEA gt
255. mpression Tension Plate FYCP FYTP Calculations for the plate flange of the frame are the same as for frame flange above Note All frame failure modes are checked at both ends of the frame segment i e at the strake edges Frame Failure Modes Collapse Collapse limit states are defined when the structure or member has failed in its primary load carrying role Frame Collapse Plastic Hinge FCPH 2009 DRS Defense Solutions LLC Advanced Technology Center 268 MAESTRO 9 0 7 8 9 2 Collapse of a transverse frame will occur if sufficient plastic hinges are formed to allow it to undergo large deformations as a mechanism In MAESTRO the strakes or evaluation patch are considered in turn and each frame segment within a strake or evaluation patch is examined at both ends If the bending moment at one of the two locations in the segment exceeds the plastic moment for that frame cross section collapse is assumed to have occurred for that frame segment The basis of this assumption is that if a plastic hinge is formed in one frame segment then the adjacent segments will be heavily loaded and the formation of sufficient plastic hinges for a mechanism will require little extra load Also and more importantly requiring only one hinge covers all of the various multi strake modes of transverse collapse ALPS ULSAP The following capability is an optional MAESTRO module Run Fast Lock if you are not certain have p
256. mum Value Plate PCSF Collapse Stiffener Flexure PCCB Collapse Combined Buckling PCMY Collapse Membrane Yield PCSB Collapse Stiffener Buckling PYTF Yield Tension in Flange PYTP Yield Tension in Plate PYCF Yield Compression in Flange PYCP Yield Compression in Plate PSPBT Serviceabilty Plate Bending Tran PSPBL Serviceability Plate Bending Long PFLB Failure Local Buckling Mimimum Value Beam GCT Tripping GCCF Collapse Compression in Flange GCCP Collapse Compression in Plate G F YCF Yield Compression in Flange G F YCP Yield Compression in Plate G F YTF Yield Tension in Flange G F YTP Yield Tension in Plate FCPH Collapse Plastic Hinge Minimum Value All Negative Positive ULSAP All Load Cases Minimum Value Plate PCPM Plate induced failure at Midspan PCCB Overall Grilage Collapse PCPE Plate induced failure at Panel Edges PCSB Stiffener induced failure tripping PCWB Panel Collapse Web Buckling PYM Yield in Mid Plane PYF Yield in Flange PYP Yield in Plate Mimimum Value Beam BCT Tripping BYC Gross Yielding BCWB Web Buckling BCC Collapse Beam Column FCPH Collapse Plastic Hinge Minimum Value All Negative Positive Selecting one of the parameters will display the patches colored by their adequacy parameter value MAESTRO can automatically display each elements smallest adequacy 2009 DRS Def
257. n m3 fr70 73 93144 3 1391 71 77 5474 7 83947e 015 top s2 midbody m2 r49 63 18939 8 1570 96 82 3971 1 87559e 014 top s3 stern ml fr63 65 260905 915 796 72 7569 7 69649e 015 top s2 midbody mi fr 25 49 28355 6 542 067 77 3852 1 21798e 014 top s1 bow m6 fr21 25 4112 36 94 0377 97 2812 3 44927e 015 top s1 bow m2 fr3 5 38284 6 423 341 80 4336 0 726928 top s1 bow mS fr15 21 25028 6 297 575 84 4411 7 88505e 015 top s1 bow m4 fr10 15 20181 2 177 04 92 1842 6 35634e 015 top s1 bow m3 fr5 10 3655 53 40 7391 115 769 8 43551e 016 top s1 bow ml fr1 3 708493 924 837 116 622 0 0392808 gt Total Module Weight Full Ship Exclude Tank Weight 708493 924 837 116 622 0 0392808 gt Total Force due to Weight Full Ship 7084941b sxaxxxeexSummary of Module Gross Weight Exclude Volume and Bay Set Weight WEIGHT 1b XCG in YCG in ZCG in Module Name 119587 272 849 a 414 3 44497 01015 e m1 4 gt Command Output Grid id h Le ET 4 9 Results Menu The Results menu allows the user several options to display and post process the results from the finite element analysis Deformed Model Stress gt Adequacy List gt Export Output gt Contour Deformed Model This option will toggle on and off whether the model is displayed as deformed or undeformed A check mark will appear next to this option in the menu if the model is in the deformed view The Deformation Scale can be adjusted in the View Optio
258. n of the graph This will produce a text box with graph data Further the user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph entity of interest 2009 DRS Defense Solutions LLC Advanced Technology Center General 89 Tor Ring 1 62E 007 1 52E 007 1 42E 007 1 12E 007 1 01E 007 9 13E 006 8 11E 006 7 10E 006 6 09E 006 al 5 07E 006 4 06E 006 3 04E 006 2 03E 006 1 01E 006 0 00E 000 View Horizontal gt The View Horizontal menu has several options to display the horizontal properties of the modeled structure A detailed description of each of these options is below Shear Force Bending Moment Net Force Shear Force Bending Moment Net Force The View Horizontal gt Net Force option is used to display the FE Model s horizontal net 2009 DRS Defense Solutions LLC Advanced Technology Center 90 MAESTRO 9 0 7 force distribution Further MAESTRO echoes this distribution to the Output window which is found at the bottom of the MAESTRO GUI In conjunction with the View Horizontal Net Force command the user can use the Dynamic Query which can be initiated via the ty icon to query the distribution graph To use this functionality the user must select the View Horizontal Net Force command toggle the Dynamic Query icon and move the mouse cursor over
259. n the List Box saying that Constraint Set 2 is the second Constraint Set in General Group 1 11 In the second box select Constraint Set 3 recall that this was BBS gt 12 12 Click on Add which generates the fifth line in the List Box saying that Constraint Set 3 is the third Constraint Set in General Group 1 13 In the second box select LOCAL 14 Click on Add which generates the sixth line in the List Box saying that the LOCAL option is the fourth Constraint Set in General Group 1 This means that the strakes defined in General Group 1 the side panels strakes 2 and 3 will have only Local optimization not Dual Level optimization 15 Click on Apply to preserve this definition of these two groups This is like the Modify button in other Dialog Boxes 2 9 Choice of Initial Values of the Design Variables With MAESTRO the initial scantlings are arbitrary They do not need to satisfy all or indeed any of the constraints But it is preferable to select values that at least appear to be reasonable because to do otherwise increases the number of design cycles required for convergence If anything it is best to be conservative because convergence is slightly faster from the feasible side A good approach is to use whatever values may be available from existing similar structures and to make a best estimate for the other values In fact the latter provides an interesting and challenging opportunity to try out one s design eye and to th
260. n the design Therefore in order to demonstrate how MAESTRO can accommodate such a limit the pontoon will be required to have a moment of inertia of at least 3 0x105 ins This is specified in the MIN IMOD line of the Other subpage 2 Minimum required value of section modulus of the module MIN ZMOD This constraint limits the maximum stress due to vertical bending of the module For example a ship s hull is subjected to long term cyclic bending due to waves and it may be desired to limit the cyclic stress to avoid fatigue In this example the module is required to 2009 DRS Defense Solutions LLC Advanced Technology Center 332 MAESTRO 9 0 7 have a minimum section modulus of 15000 ins This value is specified in the MIN ZMOD line of the Other subpage Group Optimization Settings Overall Defaults Constraints Structure 10 f00002 y Name Constraint Set 00002 Create Delete Modify Plate Girder Frame Stiffener Other Limit State Add Remove Coef 1 0 7 1 MINZMOD RHS gt 1 15000 300000 1 The above figure shows the Other subpage after the MIN IMOD and the MIN ZMOD constraints have been defined The first of these was generated by the following six steps Again if you perform these steps you will be generating a new line and the 7 step will delete it 1 Click on Add A new blank line appears in the List Box Click on Co
261. n the general purpose cost function this is defined as A A Cy P ABtp 18 hwtm by ty Pz Is in which s is the number of stiffeners 2009 DRS Defense Solutions LLC Advanced Technology Center 326 MAESTRO 9 0 7 t has tws Dy and ty are the panel scantlings A is the length of the module d is the section spacing B is the width of the strake mean value if tapered Lis the stiffener length in each panel 1 B if transversely stiffened is the volumetric cost coefficient cost per unit volume for a stiffened panel 2 1s the lineal cost coefficient cost per unit length of stiffener for a stiffened panel Girder Cost C cost of girder for each strake given by Ce dN P3 hgwtgw bef tot p4 where is the volumetric cost coefficient for fabricated beams zis the lineal cost coefficient for fabricated beams Lt N is the number of girder segments elements in the current strake if no elements are deleted this is Frame Cost C cost of the frames for each strake given by Cr Ne BID hwtw bg te Pal where N is the number of frames per strake 2 2 4 Cost Coefficients The above function contains four coefficients gt and Their default values are defined in the Module Opt Settings Dialog Box and alternative values can be specified for individual strakes The lineal cost per unit length coefficients would reflect such items as welding costs and would influen
262. nalysis type Refine Element Toolbar The Refine Element toolbar which is located on the right side of the modeling space is used to quickly and easily convert coarse mesh elements into finer mesh elements B This icon allows the user to double click a strake panel and MAESTRO will automatically convert it to a quad element This icon allows the user to double click a quad element and MAESTRO will automatically split the quad into two quads El This icon allows the user to double click a quad element and MAESTRO will automatically split the quad into three quads E This icon allows the user to double click a quad element and MAESTRO will automatically split the quad into four quads M This icon allows the user to double click a quad element and MAESTRO will automatically split the quad into a quad and a triangle M This icon allows the user to double click a quad element and MAESTRO will automatically split the quad into two triangles This icon allows the user to double click a quad element and MAESTRO will automatically split the quad into three triangles 4 This icon allows the user to double click a triangle element and MAESTRO will automatically split the triangle into two triangles amp This icon allows the user to double click a triangle element and MAESTRO will automatically split the triangle into a triangle and a quad 2009 DRS Defense Solutions LLC Advanced Technology Center 104 MAESTRO 9 0 7
263. nation of in plane compression and a positive bending moment as shown in the figure below The total stress acting through the plating as obtained from the beam column formula would be MY par Oo Jal 6 0 PD pir Op 0 i 7 P tr tr 2009 DRS Defense Solutions LLC Advanced Technology Center 260 MAESTRO 9 0 7 C a Positive deflection t t t t t Positive BM t where p is the failure stress and the subscript tr stands for the property of the transformed section Collapse occurs when o equals the failure value which is the minimum of yield stress oy or the elastic tripping stress o Mode IlI Combined failure of stiffener and plating This failure occurs due to a large positive bending moment M which would cause a large tensile stress in the stiffener The failure is due to a simultaneous stiffener tensile yielding and compressive yielding of the plate It can be shown from the interaction curve of Figure 14 2 of 1 that the load combination required for mode III failure is given by the expression MY par m o air dun A 6 0 A Y or I I tr tr D oO Ys o ee ai A A pY far I tr While evaluating PCSF the effects of transverse compression and in plane shear are also taken into account The respective reduction factors r and r are given by Panel Collapse Combined Buckling PCCB This mode PCCB examines the longitudinal stresses in ship s structures due t
264. nd settlement thereof If an injunction or order is obtained against Customer s use of the SOFTWARE or if in Licensor s reasonable opinion the SOFTWARE is likely to become the subject of a claim of infringement or violation of a U S patent copyright or trade secret then Licensor will at its option and expense i procure for Customer the right to continue using the SOFTWARE ii replace or modify the SOFTWARE so that it becomes non infringing or iii return the unamortized cost of the SOFTWARE to Customer based on a thirty six 36 month pro rata schedule TECHNICAL SUPPORT SOFTWARE MAINTENANCE User Support and Upgrades are available through the MAESTRO Maintenance and Support Agreement which can be purchased from Licensor or one of its designated Support Sales Dealers in accordance with the terms and conditions provided TERMINATION OF LICENSE This License Agreement may only be terminated by Licensor upon providing at least ten 10 calendar days prior written notice to Customer of any violation or default of the terms of this License Agreement by Customer Customer shall be allowed to remedy any such violation or default within the 10 day period to Licensor s reasonable satisfaction Upon termination for Customer s default all copies of the SOFTWARE and Documentation shall be immediately returned to Licensor or destroyed If Customer destroys all SOFTWARE 2009 DRS Defense Solutions LLC Advanced Technology Cen
265. neral tab Constraints Summary General D ON Wo We E Er glee Notation 0 Free OK Del Row Cancel Help 3 Click in the large white space and then select a node from the model to constrain 4 The module name and ID will automatically populate 5 The X Y Z Rx Ry and Rz boxes will be automatically filled with Os meaning a free condition Double click in the box to apply a fixed condition 1 or forced displacement 2 per the Notation key The DX DY DZ DRx DRy and DRz values specify the value of forced displacement if any 6 Repeat steps 3 5 to add additional constraints 7 Select OK to save Model Integrity Checks Quick Reference Wetted Elements Check Element Pressure Side Check Aspect Ratio Check Internal Angle Check Warped Quad Check Overlapped Elements Check Free Edges Check Element Connectivity Check Routine model integrity checks are a simple and time saving process It can be beneficial to conduct integrity checks after each module is completed instead of trying to check the entire model at once when it is completed 2009 DRS Defense Solutions LLC Advanced Technology Center Checking The Model 181 The following tutorials show how to exercise several common model integrity checks Menu View gt Wetted Elements 1 This integrity check can be performed from the View gt Wetted Elements menu option 2 All elements in the current view not defined as wett
266. ng and Post Processing 283 If a patch is in a perfect initial condition the user has to define a set of ultimate limit state parameters with zero imperfection If all patches are in a perfect condition then the user does not define any set of ultimate limit state parameters How do you get the ULSAP text output file for an individual patch 1 Open the Limit State Creation Evaluation dialog box 2 Select the radio button ULSAP 3 Click the ULSAP text output checkbox 4 Click Compute and then follow the result processing instructions How do you associate a set of ultimate limit state parameters to a patch 1 Define a set of ultimate limit state parameters 2 Open the Limit State Creation Evaluation dialog box 3 Select the radio button ULSAP 4 Select the parameter set 5 Click Modify How do you create a MAESTRO Scalable Solver Limit State Data 1 Manually define a patch from a general group 2 Associate the patch to a set of limit state parameters 3 Click Modify 4 Export the MAESTRO Data 8 11 Viewing Stress in a Given Direction The following tutorials shows the process of viewing element stresses in a given direction once the model is solved and the results are loaded 1 Create a general group for the plate elements of interest 2 Define the top layer fiber orientation a Right click on the group name in the group tab of the parts tree and select Modify b Check the
267. nge Fixed Rows Run Maestro Scalabe Change Font Mouse Wheel The wheel button is used to zoom and pan in your modeling space without using any MAESTRO commands Roll Wheel Rotate the wheel forward to zoom in and backwards to zoom out Use the Shift and CTRL key to accelerate zooming 2009 DRS Defense Solutions LLC Advanced Technology Center 116 MAESTRO 9 0 7 4 15 Hold Wheel Hold down the wheel button and drag the mouse to dynamically spin the model around Hold Wheel Hold Shift Hold down the Shift key and the wheel button then drag the mouse to dynamically pan the model Hold CTRL Single Click Wheel Hold the CTRL key down and then single click the wheel button this combination invokes the Cutting Planes command Keyboard Shortcuts View Options lt Esc gt key invokes the cancel command lt Ctrl n gt Endpoints and Additional Nodes dialog lt Ctrl e gt Finite Element dialog lt Ctrl k gt Strake dialog lt Ctrl d gt Deletion dialog lt Ctrl g gt Groups dialog lt Ctrl r gt Restraints dialog lt Ctrl l gt Loads dialog Menu View gt Options The View Options dialog allows the user to control a wide variety of viewing options including element node visibility rendering algorithms viewport layout etc The View Options dialog can be launched from the toolbar or from the View gt Options menu 2009 DRS Defense Solutio
268. nge the method of Beams Attached to Plating from the default Eccentric Beam to Hybrid Beam Example cd lsystem modeler90 exe ex1 mdl hybrid Keyword iterative Used to launch the Iterative solver Note the user is to define the number of iterations and tolerance If an iteration number and tolerance are omitted the number of iterations and tolerance default to 20 000 and 1 0E 5 respectively Example cd lsystem modeler90 exe ex1_iter madl iterative 2000 2 0E 6 Keyword maestro Used to perform limit state analysis using MAESTRO Example cd system modeler90 exe ex1_maestro mdl maestro Keyword nostress Used to turn off stress calculations during batch processing Example cd lsystem modeler90 exe ex1 mal nostress Keyword noreaction Used to turn off reaction force calculations during batch processing Example cd lsystem modeler90 exe ex1 mdl noreaction Keyword nolog Used to turn off the functionality that generates a log file containing the results Example cd system modeler90 exe ex1 mal nolog Keyword ulsap Used to perform limit state analysis using ALPS ULSAP Example cd lsystem modeler90 exe ex1_ulsap mdl ulsap Post processing 2009 DRS Defense Solutions LLC Advanced Technology Center 314 MAESTRO 9 0 7 The following keywords are used to access results for a given model load case and fetag so the user can compare the values to a known
269. ns LLC Advanced Technology Center General 117 View Options Labels amp Entities Visibility Plot Legend EndPaints Off Master Elements v On Fonts sans serif af Additional Nodes Off Plate Offset Off Color white v Strake Labels Off BETETE M of DE Strake Plates lv On ize Strake Frames On Scale Width 2 Strake Girders vV On Water Plane Width 1 Stiffeners Off Constraint Compounds F On onstraints 5 Quads M On Point Loads 0 Triangles M On Beams de Paint Moments 0 REEE Iv On Markers 2 Springs M On RSplines F On Spring RSpline 1 Brackets VF On Apply Defined Range Blocks 16 Pre Postprocessing Deformation Scale Rangeilhf in 2 Tools amp View Style Corner Stress Off Viewports Video Driver Options e aaiye ALPS HULL Off f Single Hardware Z buffer Shrink Elements Split Vertical M Construction Geometry Split Horizontal Advanced V Cutting Planes C Four Views M World Axes __ Cancel Labels amp Entities Visibility The view of the elements listed in the dialog can be toggled On and Off by clicking the check box Several of the elements can also be toggled to On w label which will show element IDs Water Plane CGs or Strake IDs Scale The Scale section of the View Options dialog allows the user to scale the graphic view of several entities For example the Constraints scale can be used to lengthen the graphic representation of the
270. ns dialog under the Post Processing section 2009 DRS Defense Solutions LLC Advanced Technology Center General 95 Stress gt For each load condition MAESTRO calculates stresses for all finite elements The menu items below provide access to recovering stresses in rods beams bare plates and stiffened panels An important distinction between each element type s stress recovery will be discussed in the Stress Results sections as well as additional details for each of the stress recovery options The dynamic query icon canbe used to highlight and recover a specific element s analysis results Double clicking the element will echo the results to the Output tab Note the scale for the graphical representation of stress will remain the same if switching between load cases unless the maximum stress value is higher than the current scale s maximum value To view the load case specific legend turn off the stress view and then turn it on again Mid X Normal Mid Y Normal Plate Mid XY Shear Plate Mid Von Mises Top gt Bottom Beam gt Directional Define Direction Show Direction Directional This option will toggle on or off the directional stress option Define Direction This option will launch the Define Stress Direction dialog Show Direction This option will toggle on or off whether small quills are placed on each element defining the element s local X direction Adequacy gt
271. nt type The Named View menu can be launched from the View gt Set View gt Named View menu be loaded later In addition to saving the model orientation the Named View will save the or by right clicking in the modeling space and selecting Named View MAESTRO allows the user to create their own model orientation view and save this view to Named View a a Create Modify Close Select Creating a New Named View 2009 DRS Defense Solutions LLC Advanced Technology Center 112 MAESTRO 9 0 7 4 14 Set the model to the orientation and options desired Open the Named View dialog Type a name into the drop down menu Click the Create Modify button RQ ED cee Modifying a Named View 1 Setthe model to the new orientation and options desired 2 Open the Named View dialog 3 Select the Named View from the drop down menu to modify 4 Click the Create Modify button Selecting a Named View 1 Open the Named View dialog 2 Select the desired view from the drop down menu 3 Click the Select button Deleting a Named View 1 Open the Named View dialog 2 Select the desired view from the drop down menu 3 Click the Delete button Using the Mouse amp Shortcut Keys Left Mouse Button Right Mouse Button Mouse Wheel Keyboard Shortcuts 2009 DRS Defense Solutions LLC Advanced Technology Center General 113 Zoom roll wheel lt
272. nter 166 MAESTRO 9 0 7 5 Checking Top Down can be used to create a rigid link between a coarse mesh and fine mesh model If Top Down Auto is selected the slave nodes of the fine mesh model between the two master nodes in the coarse mesh model will be automatically added 6 Click Create This procedure can be repeated to create additional rigid spline elements Toolbar Menu Model gt Elements gt Create Modify gt Bracket This tutorial shows the procedure for creating a bracket element 1 Begin by opening the Finite Element Bracket dialog using the Model gt Elements gt Create Modify gt Bracket menu the toolbar or clicking the Bracket tab in the Finite Elements dialog box Finite Elements Spring Rod Beam Triangle Quad RSpline Bracket Ei Connectivity Beam 1 Beam 2 Property M UserDefine Leg1 in Leg2 in Property v ID v Create Modify Delete 2 Make sure the appropriate module is set as the current part and click the ID button to assign a unique ID to the element 3 Click in the Beam 1 box and click the two beams that will be connected by the bracket element 4 Select a property from the drop down box or click Property to define a new one 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 167 5 Check the User Define box if you want to define the length of Leg 1 and Leg 2 ofthe bracket
273. ntour plot will reflect the current selection Define Range From List Curvature Mom SigXX Yield VonMises Yield Failure Mode SigXX SigYY SigXY SigVM Step 1 Mom 14490 2 lbfin Step 2 Mom 1 44908e 007 lbfin Step 3 Mom 2 95484e 007 Ibfin Step 4 Mom 4 43154e 007 lbfin Step 5 Mom 5 90824e 007 lbfin Step 6 Mom 7 38493e 007 lbfin Step 7 Mom 8 86162e 007 lbfin Step 8 Mom 1 03383e 008 lbfin Step 9 Mom 1 1815e 008 lbfin Step 10 Mom 1 32917e 008 lbfin The Define Range From provides a mechanism to choose what Step first appears in the menu post processing menu The user can also echo the complete Curvature versus Moment results to the Output tab which can then be plotted using 3rd party applications Finally the user can animate the progressive collapse analysis i e step through each increment by clicking the 7 icon 2009 DRS Defense Solutions LLC Advanced Technology Center 278 MAESTRO 9 0 7 8 9 4 8 9 5 Running Standalone Evaluation Standalone evaluation can be run be accessing the Limit State Creation Evaluation dialog and following the procedure outlined in Using Evaluation Patches Post processing Failure Modes wen LS Post processing of the various failure modes can be accomplished by accessing the Results gt Adequacy menu The adequacy parameters menu will be different depending on whether MAESTRO or ULSAP evaluation is chosen MAESTRO All Load Cases Mini
274. o and the right hand side being the limit value V1 Double click in the Operator cell to toggle between min max gt and lt Some sample constraints are given in the Girder subpage shown above The first constraint prevents the height of the girder web from being more than 50 times the web thickness to prevent web 2009 DRS Defense Solutions LLC Advanced Technology Center 330 MAESTRO 9 0 7 buckling The second constraint requires that the girder web height must be at least 10 larger than the frame web height in order that the flanges do not intersect thereby avoiding a complicated welded joint The third fourth fifth and last constraints involve both a lower and an upper limit on a ratio V1 and V2 The second to last constraint prevents the stiffener web thickness from being more than twice the thickness of the plating because a large difference in thickness causes an unbalanced heat input during welding If a fixed value is to be imposed this may done by means of an equals sign For example if it was desired to fix the girder web thickness at 0 25 inches this could be done by adding the following line TGW 0 25 An alternative is to freeze any design variable to its current value For constraints in which the left hand side is a design variable freeze is an additional operator as shown in the first line of the above figure The Frame and Stiffener subpages are similar to the Girder su
275. o hull girder bending This failure algorithm examines the elastic overall panel buckling due to any combination of longitudinal stress o transverse stress o and shear stress t The strength ratio RPCCB for this combined buckling constraint is calculated by using an interaction formula to combine the strength ratios for longitudinal buckling transverse buckling and shear buckling for the panel 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 261 The algorithm first calculates the uniaxial elastic critical stresses Oy or and To based on the theory in Chap 13 of 1 It then formulates the uniaxial strength ratios Rx 6 6 X Cr R 06 0 and R 1 t and inserts these into the following formula for the total interactive strength ratio o 625 1 a R R R 1 a 1 R The elastic buckling modes for a stiffened panel are presented in chapter 13 of Ref 1 Panel Collapse Membrane Yield PCMY This failure mode checks for any yielding that occurs through the thickness of the plating membrane yield When yielding occurs in any part of the strake it can easily extend into a significant portion of the structure and could lead to overall collapse MAESTRO evaluates PCMY using the Von Mises equivalent stress which is obtained by using the mean longitudinal stress acting on the panel the mean transverse stress and the shear stress as a
276. oad effect the lengthwise distribution of mass must be accounted for early in the design and should be modeled as accurately as possible at all stages of the design Ideally in a three dimensional model the masses should be placed at their actual locations using whichever of the methods presented here volumes bays module nodal plate is most appropriate for each type of mass But at early stages of design some masses may be known or estimated only in the form of a one dimensional distribution along the length of the structure and the Section definition option is intended for this and only this because it is very approximate In the Section option the one dimensional mass distribution is specified as a target value of mass per length for each section interval of selected modules For each section interval the program converts this target value of distributed mass into point masses at the endpoint generated nodes in each of the two sectional planes at the boundaries of that section interval Hence the selected modules must be orientated lengthwise in the structure Transverse modules such as a transverse bulkhead should not be included With this option there is no flexibility in choosing the nodes within each section YZ plane the program uses all of the endpoint generated nodes and it allocates the point masses in proportion to the structural mass of the strake based elements panels girder segments and frame segments attached to tho
277. oad case The Percentage column defines the percentage corroded of the specified corrosion group 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 Analyzing and Post Processing 228 MAESTRO 9 0 7 8 1 Analyzing and Post Processing The topics in this section provide detailed information on the MAESTRO functionality used for analyzing and post processing a model Solver Types MAESTRO offers three solver methods for coarse mesh model analyses Sparse Iterative and Skyline Fine mesh model analyses use the Sparse solver method MAESTRO also offers two beam elements for handling the effect of beam bending on in plane response an Eccentric Beam element and a Hybrid Beam element Analysis Evaluation Static Analysis Equation Solver Method Sparse C Iterative C Skyline Beams Attached to Plating fe Eccentric Beam C Hybrid Beam Stresses amp Reaction Forces M Calculate Stresses M Calculate Reaction Forces Failure Mode Evaluation None C MAESTRO C ULSAP Salve All Fine Mesh Models Sparse Solver MAESTRO s Sparse solver method uses the Intel Pardiso sparse solver and is the default and most commonly used solver within MAESTRO The package PARDISO is a 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 229 high performance robust memory efficient and easy to use software for solving larg
278. oading as well as of geometry Because of this the results for strake 3 should be the same as for strake 2 and the results for strake 4 should be the same as for strake 1 In this module there is a transverse bulkhead at each end modeled with two additional panels and stiffened by two additional beams as always the word additional means not strake related 1 3 Boundary Conditions For Modules In this example the boundary forces are the bending moment and shear force that act at the end of the module In ships and in box girder bridges this information can be obtained from a prior and relatively simple analysis of the overall structure because it is essentially a beam This is not possible with a semi submersible because of the interconnection between pontoons columns and deck structure For such a structure the MAESTRO model would initially at least include however much of the structure is necessary in order to have known boundary conditions This would be either the entire structure or depending on the degree of 2009 DRS Defense Solutions LLC Advanced Technology Center Tutorials 321 symmetry one half or one quarter of it In most applications of MAESTRO this overall model is the only model that is required Since all of the modules are in the model they interact fully just as in the real structure Hence each module always has the correct boundary conditions 1 4 Boundary Forces For This Ex
279. ocess Import programs that are searching for a particular ENTITY type can search the file for the string SENTITY and then read the next line to see if the type is correct and go on from there Data tags items preceeded with must have the in column 1 i e no white space is allowed before a data tag Leading white space tabs spaces is allowed on lines containing data Blank lines are allowed between data and the next data tag Any data that is shown in the entity definitions is required if not known dummy data should be substituted Where entities allow for more than one body or surface it is subdivided into parts each part may represent a body or surface or a group of bodies Entity 1 Sectional Data SECTIONS Note Indenting is for clarity only not used in actual data file IDF 3 01 or greater SENTITY SECTIONS VESSEL NAME Identifier for this vessel DATA SOURCE program that wrote the file DATE mm dd yy 2009 DRS Defense Solutions LLC Advanced Technology Center Appendices 393 TIME hh mm ss SUNITS This line must be either SI or User Defined If User Defined then the following line s must be specified of user units meter COORDINATE SYSTEM coordinates of a point one unit forward starboard down coordinate gnomon e g for FAST SHIP 1 1 1 COMMENTS This is a comment about the ship about to be described Can be any of 79 character lines GEOMETRY n n
280. odel gt Stiffener Layout 2009 DRS Defense Solutions LLC Advanced Technology Center 150 MAESTRO 9 0 7 Stiffener layouts allow the user to define the number of stiffeners or breadth between stiffeners for a panel element Stiffener properties are defined in the beam properties dialog box Stiffeners are defined as beam elements but they are not actual finite elements in a coarse mesh model Instead they are treated as additional stiffness in the defined direction for the panel element they are defined on thus converting the material to orthotropic In a coarse mesh model all stiffeners are treated as internal regardless of their defined location The number of stiffeners whether defined as internal or edge is the key to how the mechanical properties of the panel element are changed However the location is relevant when creating a fine mesh model from the coarse mesh model At this point an actual beam element will be created representing the properties of the stiffener at the defined location As a result of MAESTRO s treatment of stiffeners there are a couple caveats when defining stiffened panels e An edge stiffener defined in a coarse mesh model on the centerline will not be flagged as a centerline element Instead it will be treated as if there are two stiffeners with identical properties thus affecting the total stiffness cross sectional area etc e Similar to the point above stiffeners may be m
281. odeled as overlapped and MAESTRO s integrity check will not recognize this For example two consecutive strakes may each have a stiffener on their shared edge or a transverse stiffener layout with edge 1 and edge 2 stiffeners defined could be applied to a strake thus creating overlapped stiffeners Again this will be treated as if there are two stiffeners with identical properties thus affecting the total stiffness cross sectional area etc In the coarse mesh model stiffeners are shown graphically with a red line representing their location and orientation Stiffeners can be toggled on or off in the View Options dialog or with the Stiffeners On Off icon T This tutorial shows the procedure for defining stiffener layouts that can be applied to a strake panel or an additional quad element 1 Begin by opening the Stiffener Layout dialog box from the Model gt Stiffener Layout menu or from the toolbar The dialog can also be accessed from within the Strakes dialog box or the Fine Elements dialog on the Quad tab 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 151 Stiffener Layout Identification Name x ID nd Property Property MAESTRO Settings Number of Internal Stiffeners 0 Edge 1 Stiffener C Breadth Between Stiffeners Edge 2 Stiffener Create Modify Delete Close 2 Click ID to create a new layout 3 Give the layout a descriptive name
282. of gravity aft of the FP XLWL location of length on waterline Distance of the forward most point of LWL aft of FP Registers location of LWL with respect to FP XLPRC location of projected chine length Distance of the forward most point of LPRC aft of FP Registers location of LPRC with respect to FP Entity 5 Sectional Area Data AREA Note Indenting is used for clarity only not used in actual file IDF 3 01 or greater SENTITY AREA VESSEL NAME Identifier for this vessel DATA SOURCE program that wrote the file DATE 2009 DRS Defense Solutions LLC Advanced Technology Center Appendices 403 mm dd yy TIME hh mm ss SUNITS This line must be either SI or User Defined If User Defined then the following line s must be specified of user units meter of user units square meter COORDINATE SYSTEM coordinates of a point one unit forward starboard down coordinate gnomon e g for FAST SHIP 1 1 1 COMMENTS This is a comment about the ship about to be described Can be any of 79 character lines GEOMETRY n number of parts or surfaces part 1 part n where each part is PART part name nsta xl al x2 a2 2009 DRS Defense Solutions LLC Advanced Technology Center 404 MAESTRO 9 0 7 xnsta ansta where nsta is the number of stations cutting the part xi is the ith station s longitudinal coordinate and ai is it s imme
283. of the ALPS HULL module is that it can accommodate the effects of all possible hull girder sectional load components i e vertical bending horizontal bending vertical shearing force horizontal shearing force and torsion in addition to local pressure loads in the ultimate strength calculations Creating an ALPS HULL Model The progressive hull girder collapse model is a hull girder cross sectional module with one frame length This one bay module should only consist of quad and bar elements such as the one shown below The plates and webs of the longitudinal girders should be modeled as non stiffened quads bare plate while stiffeners and girder flanges can be modeled as bar elements The hull girder collapse model can be generated manually or automatically from the global model by using MAESTRO s refinement functionality 1 Open the sample ALPSHULL_0O mal which is located in the C Program Files MAESTRO Models and Samples directory You will notice that this model is a half model which is a common starting point for users The steps below will demonstrate how to arrive to a full model which is required for the progressive hull girder collapse analysis 2 Create a general group of the section i e one frame spacing of interest from the global 2009 DRS Defense Solutions LLC Advanced Technology Center 272 MAESTRO 9 0 7 model as shown below Click here to learn about creating general groups Volume
284. of the two module level constraints discussed earlier 2009 DRS Defense Solutions LLC Advanced Technology Center 338 MAESTRO 9 0 7 2 10 Running the Job and Viewing the Output File We are now ready to run the job The progress of the job and later the job output file will be displayed in the Output pane of the Modeler display which can be viewed by clicking on the Output tab at the bottom left corner of the display Then make the Output pane larger by placing the cursor on the border between the Viewport and the Output pane until you get a double headed arrow and move the border up so that the Output pane nearly fills the entire display Now go to the execution toolbar at the far right of all the toolbars along the top and click on the Run Coarse Mesh button 7 the MAESTRO logo You will be asked if you want to overwrite the input file EX2 DAT The usual response is Yes in order that the file will reflect any and all changes you have made in the model by means of the Modeler However sometimes there are reasons to make a change to the DAT file by editing it directly instead of using the Modeler In that case you would answer No Click on Yes In the Output pane MAESTRO will display its progress as it runs through the three optimization cycles and the final evaluation cycle that we requested in the Job Info Dialog Box see Section 2 1 When finished it will ask if you want to load the result Click on
285. og All This option will graphically display all the boundary nodal forces and moments applied to the model representing the vertical bending vertical shear horizontal bending horizontal shear and torsion The dynamic query nd individual nodes icon can be used to query the force and moments at Total Point Force This option provides a graphical representation of the equivalent nodal force for the currently selected load case The dynamic query fi icon can be used to query a specific node and that node can be double clicked to echo the information to the Output tab Hull Menu The Hull menu is used to display various model properties which can then be queried This provides the user with a graphical method to quickly and accurately identify trends Because graphics alone are not sufficient a majority of these menu items produce distribution data in the form of text in the Output window for further scrutiny A brief description of each option is discussed below Note If transverse symmetry is checked in the Job Information dialog the results shown will be for the full model not just the half modeled In conjunction with the Hull menu the user can use the Dynamic Query tool which can be initiated via the f icon to query the distribution graph To use this functionality the user must select the Hull menu item of choice toggle the Dynamic Query icon and move the mouse cursor over a particular portion of the graph T
286. og box The Sentinel Driver and Protection Server are now part of the MAESTRO installation and 2009 DRS Defense Solutions LLC Advanced Technology Center 386 MAESTRO 9 0 7 therefore it is no longer a separate product e Where can I get more information for troubleshooting issues with a Network lock Please see the ReadMe pof file located in the MAESTRO installation directory under System gt Sentinel for more information regarding MAESTRO network locks 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 Appendices 388 MAESTRO 9 0 7 13 13 1 Appendices Enter topic text here A References 1 Hughes O F Ship Structural Design Society of Naval Architects and Marine Engineers Jersey City NJ 1988 2 Paik Thayamballi Ultimate Limit State Design of Steel Plated Structures John Wiley amp Sons LTD England 2003 3 Mistree F Hughes O F and Phuoc H B An Optimization Method for the Design of Large Highly Constrained Complex Systems Engineering Optimization vol 5 no 3 August 1981 4 Mistree F Hughes O F Bras B The Compromise Decision Support Problem and the Adaptive Linear Programming Algorithm Structural Optimizaiton Status and Promise Kamat M P ed A I A A Washington DC 1993 pp 247 286 5 Liu D Hughes O F and Mahowald J E Applications of a Computer Aided Optimal Preliminary Ship St
287. on has converged to a final value of 0 782 page 47 a change of 21 8 from the original value of 1 000 Finally as requested in the Job Information data MAESTRO performs an evaluation cycle a finite element analysis followed by an evaluation at both levels This should normally be requested because it is the only way of being sure that the results of the last design cycle satisfy all of the constraints But this final evaluation also has a broader purpose Since the specified number of design cycles has now been completed the designer would usually want to review the results in more detail than 2009 DRS Defense Solutions LLC Advanced Technology Center 342 MAESTRO 9 0 7 before to see whether any further cycles are required and to examine aspects of special interest For example for some of the limit states especially those that were the active constraints it may be of interest to learn just where in the structure each limit state has its lowest margin and for what loadcase Are several of them clustered in one location Do they occur in the same loadcase What particular combination of load effects is involved and what are their magnitudes As with the optimization results this type of information gives the designer a clearer and more complete view of the structure and may generate ideas for further improvements In order to provide this information the output of the evaluation cycle is usually more detailed t
288. on will be automatically calculated by selecting Default or it can be specified by the user This functionality can be useful if the model will not balance and user wants to specify a center of flotation close to the expected in order to get the balance to solve The Emergence Heel Angle and Pitch Angle will automatically update if the MAESTRO balance function is used to place the model in an equilibrium position 7 4 9 Constraint Tab LoadCase 001 v Name LightShip z General Mass Point Force Pressure Balance Constraint Y sym Z sym X Asym Y Asym Z Asym module lightship v Add Group gt aje Modify Del Row Close Help The Constraint tab is activated by selecting the Re define Constraints box found under the General tab of the Loads dialog box This allows the user to override any constraints initially defined if any and have constraints specific to each load case 2009 DRS Defense Solutions LLC Advanced Technology Center 226 MAESTRO 9 0 7 7 4 10 Corrosion Tab LoadCase 001 v Name LightShip z General Mass Point Force Pressure Balance Constraint Corrosion v Add Group ID Group Name Percentage Modify Del Row Close Help The Corrosion tab is activated by selecting the Corrosion box found under the General tab of the Loads dialog box This allows the user incorporate the pre defined corrosion groups into a particular l
289. onstration of this Post Processing e With respect to stiffener tripping calculations are the stiffeners defined in the stiffener layouts taken to be normal to the strake Yes MAESTRO s stiffeners are normal to the plate e How does Yield Stress as defined in the Materials dialog affect the analysis 2009 DRS Defense Solutions LLC Advanced Technology Center Frequently Asked Questions 385 Yield stress only affects the analysis when using the limit state analysis e What is the Master Elements option used for in the View Options dialog Master elements are the parent elements of fine mesh elements This can be used when a user wants to view the fine mesh results in the context of the global model by clicking View gt All Modules Turning off Master Elements allows the fine mesh elements to be more clearly seen e When performing a natural frequency analysis how do you view the participation factors and what do they indicate A summary of the analysis can be seen in the output tab at the bottom of the screen ACU is the accumulated modal participation factor Modal effective mass and participation factor are relative measurement to the total vibration For example if the ACU is 99 in the first five modes it implies the first five modes are dominant modes and the rest of the modes can often be ignored Modal effective mass and participation factors are often used in constraint vibration such
290. ontacted by a MAESTRO sales representative and a quote will be generated for the requested modules or maintenance and support extension You may also contact the DRS C3 ATC directly 160 Sallitt Drive Suite 200 Stevensville MD 21666 Phone 410 604 8000 Fax 410 643 5370 Email sales orca3d com Getting Started The current release of MAESTRO can be downloaded from http www orca3d com maestro download htm 2009 DRS Defense Solutions LLC Advanced Technology Center Introduction 23 Once the download is complete double click the self extracting file MAESTRO Installation _v9 0 6 exe to start the installation process Follow the on screen instructions to complete the installation With MAESTRO version 9 0 and later the installation will automatically ensure the appropriate drivers and servers for network licenses are installed Once the MAESTRO installation is complete verify that the license dongle USB or parallel port is attached to the local machine where MAESTRO is installed or if it is a network license that the dongle is attached to the host computer and the Sentinel Protection Service is started on the host computer This can be verified by opening the Control Panel clicking on Administrative Tools and then Services If the service is not already started start the service before launching MAESTRO to ensure the network lock is found If you do not have a license or your current license is expir
291. ontrol and without its fault or negligence 12 GOVERNING LAW ARBITRATION This License Agreement shall be governed by and construed under the laws of the State of New York U S A excluding its conflict of laws principles Any dispute controversy or claim arising out of or relating to this License Agreement or a breach thereof shall be finally resolved by arbitration Such arbitration shall be the parties exclusive remedy except for cases of urgent equitable relief The arbitration shall be in accordance with the rules of the American Arbitration Association AAA then in effect on the date of this Agreement by one arbitrator appointed in accordance with such rules In the event of any conflict between the rules and this clause the provisions of this clause shall govern Unless the parties otherwise mutually agree in writing the place of arbitration shall be New York New York U S A The arbitration shall be conducted in the English language The parties shall pay their own arbitration expenses and shall equally share the arbitrator s costs and fees and the arbitrator shall allocate such costs equally between the parties as part of the award 13 LIMITED LICENSE FOR TRIAL RELEASE Licensor hereby grants Customer a limited non exclusive non transferable right to use the SOFTWARE at no charge for the limited purpose of evaluating whether to purchase the SOFTWARE This trial release license contains the following requirements restrictions
292. ormation General Structure Origin amp Balancing Units Criteria Comments Job Title feanogider Job Type Analysis Optimization EF Design Cycles 3 Save Deflections 0 Deflections Available Preliminary D F Scantlings Available Strake Opt Cycles fo M Save Scantlings Output Level Normal ExtendedLevelforLast 0 cycles C Extended Optimization Output Level jo x Cancel Help 5 Also in the Job Information Dialog Box specify that a restart file should be generated by checking the Save Scantlings check box as shown in the next figure it is probably already checked Keep the number of design cycles at 3 so that the new restart file has all 3 cycles Click OK Now we must run MAESTRO in order to create the new restart file consistent with the deletion of the girders That is we are repeating the first three cycles but with no girders 6 Click on the execute button at the far right of the upper toolbar the MAESTRO logo When asked about overwriting click Yes because we have changed the model no girders 2009 DRS Defense Solutions LLC Advanced Technology Center Tutorials 345 2 15 Job No 2 Restart Cycles 4 And 5 No Girders A restart file is a file created by MAESTRO if requested as we just did for each module that is currently being optimized Each restart file contains the initial scantlings and the new scantlings that are o
293. ormed or undeformed state 3 Click on Stress and select which stress to display Deformed Model 3 m gt 42 Mid X Normal Adequacy Mid Y Normal Plate Mid XY Shear Plate Mid Von Mises List Export Output gt Se de Top gt Bottom gt Beam gt Contour Directional Define Direction Show Direction A detailed description of each type of stress that can be recovered can be found in the Stress Results sections 4 Acontoured stress plot can be shown by clicking the Contour Plot icon I or selecting Results gt Contour from the menu Individual element deformations and stresses and nodal deformations and forces can be identified using the dynamic query function of MAESTRO 5 Click the dynamic query icon mr Deformed Model Stress g Adequacy gt List gt Export Output gt Contour 6 Select Node to query nodes otherwise select the results you would like to query from the 2009 DRS Defense Solutions LLC Advanced Technology Center 248 MAESTRO 9 0 7 element A check mark will appear next to the selected option 7 You may now highlight an element or node to view the results top 3port super structure m1 fr 57 66 strake 6 Quad Sec 9 Thickness 6 mm AvgPressure 0 N mm 2 FeTag 720 Stresses Mid N mm 2 SigX 5 1633E 001 SigY 8 2939E 002 Tau 0 187592 SigVM 6 4952E 001 Corner Stress VM1 5 6221E 001 VM2 6 6596E 001 VM3 1 85
294. orward of the substructure s origin would be defined with a module origin of X 20m Y 0m and Z 0m Defining Job Information Toolbar Menu File gt Job Information The MAESTRO Job Information dialog can be accessed from the File gt Job Information menu or from the toolbar This is where global settings and the job title can be defined 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 135 Job Information Job Title Model Characteristics Cut Model M Transverse Symmetry Nodal Join Tolerance 0 001 m Environment Density of Seawater 1025 9 kg m 3 Gravitational Acceleration 9 80665 m s Hull Girder Stations Spacing default 20 stations default m 0 Location Structural x Value default m Safety Factors Safety Factor for Collapse 1 5 Safety Factor for Serviceability 1 25 Panel Girder Frame The Cut Model option provides the ability to apply bending moments at bounding module locations This is useful if it is the intent to not generate a complete model only 0 4L amidships for example and apply bending moments at the ends The transverse symmetry option notifies MAESTRO that it is the intent to construct a half model and thus MAESTRO will automatically mirror the model about the centerline for analysis The seawater density and gravity values can be changed as desired The Hull Girder Stations allows th
295. oss yielding e Either steel or aluminum panels can be analyzed 2009 DRS Defense Solutions LLC Advanced Technology Center 16 MAESTRO 9 0 7 e Any combination of in plane load components can be evaluated namely longitudinal axial compression or tension transverse axial compression or tension longitudinal in plane bending transverse in plane bending and edge shear as well as lateral pressure load e Fabrication related initial imperfections in the form of initial deflections and welding residual stress can be accounted for with parameters of influence e Effect of softening in heat affected zone of welded aluminum panels can be taken into account e Effects of structural damages such as corrosion either general or localized corrosion fatigue cracking and local denting are dealt with as parameters of influence e Permanent set lateral deflection of plates and stiffened panels under impact pressure loads arising from sloshing slamming and green waters ALPS Hull The ALPS HULL module is for progressive collapse analysis of ship hulls applying and idealized structural unit method The main features of this module are as follows Paik Thayamballi e Progressive collapse analysis of ships under hull girder loads can be performed quickly and accurately until and after the ultimate strength is reached e Either steel or aluminum material can be analyzed e Any combination of various hull girder load
296. oss Sectional Area Neutral Axis Shear Center Warping Constant Torsional Rigidity Shear Force The View Longitudinal gt Shear Force command under the the Hull menu is used to display the FE model s longitudinal shear force distribution as shown below MAESTRO also echoes this distribution to the Output window which is found at the bottom of the MAESTRO GUI In conjunction with the View Longitudinal Shear Force command the user can use the Dynamic Query which can be initiated via the t v icon to query the distribution graph To use this functionality the user must select the View Shear Force command toggle the Dynamic Query icon and move the mouse cursor over a particular portion of the graph This will produce a text box with graph data Further the user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph entity of interest 2009 DRS Defense Solutions LLC Advanced Technology Center General 77 Shear Force lbf 8 10E 004 5 38E 004 4 47E 004 3 66E 004 2 66E 004 1 75E 004 8 46E 003 6 01E 002 9 66E 003 1 87E 004 2 78E 004 3 69E 004 4 59E 004 5 50E 004 6 40E 004 Bending Moment The View Longitudinal gt Bending Moment command under the the Hull menu is used to display the FE model s longitudinal bending moment distribution as shown below MAESTRO also echoes this distribution to the Ou
297. oth ends Enter values specified for the full cross section even ifthe model is a half model Lumped Force Reference End Opposite End Vertical Bending Moment N m Vertical Shear Force N Horizontal Bending Moment N m Horizontal Shear Force N Torsional Moment N m Modify Del Row Close Help The End Moments tab can be used to apply a prescribed bending moment shear force or torsional moment to a cut model only The cut model option can be selected in the Job Information dialog The model boundaries are defined by the Start and End Modules in the Constraints dialog The force and length units are regarded as those defined in the Units dialog Even if only half of the model is defined the values for the full cross section should be applied If a bending moment is applied to the model the MAESTRO balance command can be used to calculate the shear force A sagging bending moment is positive and a hogging bending moment is negative Shear force is positive upwards at the reference and opposite end A horizontal bending moment is positive if the resulting curvature in the model s XZ plane has its concave side in the Z direction The sign of the torsional moment applied to the reference and opposite end is governed by the right hand rule about the model s X axis 2009 DRS Defense Solutions LLC Advanced Technology Center 218 MAESTRO 9 0 7 7 4 6 7 4 7 Poin
298. ound in the same procedure as creating an additional element but instead of clicking Create click Add in the specific element tab It is a good convention to define all elements on the reference end and set them for additional sections using the Rule tab 5 Click the Rule tab 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 169 Compounds Name Compound 1 ID 00001 Spring Rod Beam Tri Quad Bracket Rule Set Rule Modifs Cmpd Delete Cmpd Close The Rule tab allows the user to set at which sections within the module the compound will be created The 0 represents the reference end and the last number represents the opposite end Checking the box for each section will apply the defined compound at that section 6 Click the Set Rule button This procedure can be repeated to create additional compounds Compounds can have elements added or deleted at any time by adding or deleting elements in their specific tabs The Modify Cmpd button is only used to modify the name of the compound The entire compound can be deleted using the Delete Cmpd button 5 14 Deleting Elements oa Tools gt Deletions gt Select Tools gt Deletions gt All Visible gt Model gt Elements gt Delete gt In addition to deleting elements in the Strakes Additional Elements or Compounds dialog 2009 DRS Defense Solu
299. ount for hydrostatic pressure mass loads etc in one load case 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 Tutorials Tutorials 319 10 Tutorials Much of the help file is mini tutorial or how to based The following full tutorials present a broader range of MAESTRO features 10 1 Basic Features This Tutorial is intended to do two things simultaneously e to demonstrate and explain some of the basic features and options of the Modeler and e to go through the steps of actually building a small model starting with 4 of the engine room of a small naval vessel 10 2 Optimization The following tutorial will walk through an example process of optimizing a box girder structure 10 2 1 Defining the Model DEFINITION OF MODEL BOUNDARY CONDITIONS AND LOADS 1 1 Making a Backup Copy of the Modeler File This document shows how to prepare the input data and interpret the output for optimization jobs This document assumes that you have already gone through the Tutorial that is available through the Help button In effect it is a second tutorial and you are invited to open the relevant Modeler file ex2 mdl and actually fill in the Dialog Boxes as shown herein To do this will require deleting the existing entries in the Dialog Boxes and then re entering the data To safeguard the original file you should first make a backup copy say ex2backup mdl Later in the tutoria
300. ouse and finally select Flip Stiffener Side 2009 DRS Defense Solutions LLC Advanced Technology Center General 49 Thickness With Corrosion Net With Corroded Beam Flange Beam Web Plate Composite Layers With Corrosion Net This option is used to toggle the view to display the thickness of Plate Beam Web or Beam Flange with or without net corrosion and is used in conjunction with the Plate Beam Web or Beam Flange menu option With Corroded This option is used to toggle the view to display the thickness of Plate Beam Web or Beam 2009 DRS Defense Solutions LLC Advanced Technology Center 50 MAESTRO 9 0 7 Flange with or without corroded and is used in conjunction with the Plate Beam Web or Beam Flange menu option Beam Flange The Beam Flange view under the Thickness menu displays the flange thickness of all beam elements in the model This helps the user to identify mistakes in the model In conjunction with the Beam Flange thickness view the user can use the Dynamic Query tool which can be initiated via the LM icon to change the thickness in a particular element To use this functionality the user must first change to the Beam Flange view toggle the Dynamic Query icon move the mouse cursor over a particular element right click the mouse and finally select the thickness of choice Beam Web The Beam Web view under the Thickne
301. ovided in the Models and Samples Advanced Programming Read Results directory 2009 DRS Defense Solutions LLC Advanced Technology Center 316 MAESTRO 9 0 7 9 2 2 9 3 Run MAESTRO Solver MAESTRO offers batch processing functionality as described in the Batch Processing section The batch processing described in this particular section describes how a user can access multiple results for custom processing To assist the user processing multiple entities and load case a sample program has been provided A sample program written in C is provided in the Models and Samples Advanced Programming Run MAESTRO Solver directory Importing Hydro Loads MAESTRO has the ability to export a wet file to be used in a 3rd party software program to create an external pressure smn file This smn file can be then imported to MAESTRO as a new load case s The samples used in the following tutorial can be found in the MAESTRO installation directory under Models and Samples Tutorials Import Hydro Loads The following is a screenshot of the ex1 smn file provided in the directory listed above The first part gives the units of the values defined in the file The file is then broken down by load cases Each load case provides the displacement and accelerations of the model The wetted elements are then listed by element ID and their calculated external pressure units ips fps nmm in lb ft lb if none unts n m units ips
302. ows the user to click in the deletions dialog and then select elements to delete by drawing a box around them Note the element filters will not hold when using the select by box option 4 The selected elements will appear in a list with their Module Name Type and ID The selected elements will also be removed in the model view To undelete an item select it from the list and click the Recover ltem button 5 Click Delete to permanently delete the selected elements 6 All visible elements can be deleted from the Tools gt Deletions gt All Visible gt menu This allows the user to delete all visible elements of a specific type Once an element is added to the Deletion dialog the user can right click on the element line and a new menu will appear with additional deletions options Deletion Full Strake Cmpd V Strake Compound Box M RSpline v Tri V Quad v Beam v Rod v Spring V Bracket Add By Prop Module Name Add By Mat 1MorucLeVautes Add By Stf Layout Add By Type New Module Return Item to Model Delete Close These options will add the elements from the current view part that have the either the same property material stiffener layout or type as the currently selected element from the dialog box Note using the right click menu does not take into account the selected element filters The New Module button will create a new module consisting of the elements added to the deletions dialog 2009 DRS Def
303. ped twisted quads element internal angles and overlapped elements These integrity checks can be executed at any stage of the process 2009 DRS Defense Solutions LLC Advanced Technology Center Introduction 19 3 1 4 Analyzing Your Model When the modeling stage is complete MAESTRO provides interfaces to solvers to perform both finite element analysis and structural evaluation Regarding structural evaluation MAESTRO provides three failure mode strength assessments which are discussed briefly MAESTRO Failure Evaluation The first is the MAESTRO failure evaluation which is based on the theory presented in Ship Structural Design Hughes The following are the modes of failure examined by the MAESTRO evaluation method Panels Panel Collapse stiffener flexure combined buckling membrane yield and stiffener bucking Panel Yield tension compression in the stiffener flange and tension compression in the plate Panel Serviceability due to local plate bending longitudinal transverse Panel Failure due to local plate buckling Girders Girder Collapse tripping and tension compression in flange Girder Yield tension compression in the plate flange Frames Frame Collapse plastic hinge Frame Yield tension compression in the plate flange ALPS ULSAP Failure Evaluation The second is the ALPS ULSAP failure evaluation which is based heavily on the theory presented in Ultimate Limit Sta
304. pen the Limit State Creation Evaluation dialog box 2 Expand the column until the name of the plate property is seen 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 281 3 Move the cursor to the plate property and right click it M Limit State Creation Evaluation Identification ID 02286 MES a C ULSAP Name Patch 000563 MAESTRO Input Data Evaluation Type C US NAY Auto Userdefine Panel Beam Column Length in Width in E 2 95877e 007 Ibf in 2 Poisson 0 3 Init Maximum Deflection in Yield 34083 9 Ibf in 2 Compressive Residual Stress Ibf in 2 Stiffener Name none Number Init Maximum Deflection in Compressive Residual Stress Ibf in 2 Breadth Heat Affected Zone for Aluminium in Stress Lower bf in 2 1318 81 6 59914 Stress Upper Ibf in 2 1318 81 6 59914 Stress Shear Ibf in 2 22 3742 Pressure Ibf in 2 Create Modify Delete Compute Close How do you modify the scantlings and stress parameters of a patch 1 Open the Limit State Creation Evaluation dialog box 2 Change the radio button from Auto to User defined 3 Enter the desired data 4 Click Modify How do you change an evaluation method 1 Open the Limit State Creation Evaluation dialog box 2009 DRS Defense Solutions LLC Advanced Technology Center 282 MAESTRO 9 0
305. pressure surface will rotate so as to remain normal to the total acceleration vector and the direction of the total acceleration will not be parallel to either the Y axis or the structure Y axis Plate Surface Zero 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 221 LoadCase Name General Mass PointForce Pressure Balance Plate LinPress Plate Surface Head Plate Surface Zero Additional Beam Edge Full Strake Compound v Add Plate Group Module Name _Type 1D_ Density kg mm3 Zero Y mm Zero Z mm gt Modify DelRow Close Help The Surface Zero option is intended for hydrostatic pressure for which the value is proportional to the depth below the free surface of a fluid or other zero pressure plane In the Surface Zero option the pressure is always an actual pressure not a design pressure For strake panels the pressure varies linearly across the strake width in proportion to the local depth below the zero pressure surface and in the lengthwise direction it is constant over each panel and is calculated separately for each panel based on the depth of that panel below the zero pressure surface For additional non strake panels and triangles the pressure is calculated at each corner of the element and then multiplied by either one fourth or one third of the element area Using the Surface Zero option the user will be expected to define the zero
306. produce a text box with graph data Further the user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph entity of interest 2009 DRS Defense Solutions LLC Advanced Technology Center General 83 zz in 4 85E 007 73E 007 62E 007 50E 007 39E 007 1 27E 007 1 16E 007 1 04E 007 9 24E 006 a 8 09E 006 6 93E 006 pm 5 78E 006 m 4 62E 006 347E 006 2 31E 006 1 16E 006 0 00E 000 lyy The View Longitudinal gt lyy command under the the Hull menu is used to display the FE model s inertia properties about the y axis for each section as shown below In conjunction with the View Longitudinal lyy command the user can use the Dynamic Query which can be initiated via the me icon to query the distribution graph To use this functionality the user must select the View lyy command toggle the Dynamic Query icon and move the mouse cursor over a particular portion of the graph This will produce a text box with graph data Further the user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph entity of interest 2009 DRS Defense Solutions LLC Advanced Technology Center 84 MAESTRO 9 0 7 lyy in 4 1 98E 007 1 48E 007 1 36E 007 1 24E 007 1 11E 007 9 90E 006 8 6
307. ptance of payment hereunder Purchase orders or other similar unilateral documents issued by the Customer shall be for the Customer s internal use only and shall not be binding on Licensor or otherwise affect or amend this License Agreement whatsoever 5 23 08 2009 DRS Defense Solutions LLC Advanced Technology Center
308. quantity If the solution quantities do not match the prescribed quantities MAESTRO will produce an error message such as the on below This is useful from a quality checking perspective Keyword adq Used to access a variety of adequacy parameters associated with structural evaluation using the MAESTRO and ALPS ULSAP limit states Note the adequacy comparisons have a built in tolerance of 0 001 Sub keywords associated ONLY with ALPS ULSAP are noted below Examples is provided below Sub keywords to adg for MAESTRO and ALPS ULSAP e Load Case Specification LC e FeTag Specification FETAG e Panel Limit States pcsf pccb pcmy pcsb pytf pytp pycp pspbl pspbt pflb e Beam Limit States bct byc bcwb bcc bccf bccp bycf bycp bytf bytp bcph e Rod Limit State euler Example cd system modeler90 exe ex1_maestro mdl maestro adq LC 1 FETAG 6 pccb 0 535 Sub keywords to adg for ALPS ULSAP only e Panel Limit States pcom pcpe Example cd lsystem modeler90 exe ex1_maestro mal ulsap adq LC 1 FETAG 6 pcpe 0 502 Keyword disp Used to access the displacement results of a given load case and fetag Note the user is to define via sub keywords the load case fetag type of displacement and tolerance An example is provided below Sub keywords to disp e Load Case Specification LC e FeTag Specification FETAG e Displacement Type dx dy dz rx ry rz dt total translation
309. r Cutting Planes gt Set Current Part Set View Part Set Current amp View Part Integrity Check Compute gt Find FE Tag Renumber FE Tag Edit Nastran Data Choose Editor Program Use Non MAESTRO Editor Toolbars gt This option allows the user to toggle on and off the view of the MAESTRO toolbars v Pre processing v Post processing v Standard Toolbar v FlagShip Toolbar v Refine Toolbar Construction Geometry gt This option opens the Construction Geometry menu which allows the user to create and delete construction lines and markers Marker gt Line Delete gt 2009 DRS Defense Solutions LLC Advanced Technology Center 34 MAESTRO 9 0 7 Cutting Planes gt This option allows the user to define a cutting plane or delete an existing one XY Plane YZ Plane ZX Plane XY Slice YZ Slice ZX Slice Specify Delete Set Current Part This option allows the user to click a part in the model space to set as the current part This is the same as clicking the Set Current Part icon Set View Part This option allows the user to click a part in the model space to set as the view part which will zoom fit the window to this part This is the same as clicking the Set View Part icon P Set Current amp View Part This option allows the user to click a part in the model space to set as the current and view part This combines the function of the Set Current Part and Set View P
310. r of elements and nodes has been moved to the Model gt Summary menu item Bug Fixes Update FE Tags Fixed a bug so that FE Tags are updated when a module or substructure is moved or rotated Collapsed Quad Fixed a bug so that a quad collapsed to a triangular element correctly distributes mass and force to the appropriate nodes e Sort Volume Table Fixed a bug so the Volume Table can now be sorted by the Volume Group Name e Deletions Dialog Fixed a bug that would cause a hard crash when deleting large amounts of elements from the deletions dialog e Sort Element List by ID Fixed a bug that allows elements to be sorted in the Grid tab without information disappearing e Sort Nodes List by ID Fixed a bug that caused a hard crash when trying to sorted listed nodes by ID in Grid tab e Warped Quad Fixed a bug to take the average face normal of the two triangles making up a warped quad for area weight volume etc calculations e Trochoidal Wave Fixed a bug so that the trochoidal wave profile definition now uses the formulas provided in DDS 100 6 i 2 e Parts Tree in Parts Dialog Fixed a bug so that the parts tree within the Modules and Substructures dialog is consistent with the main parts tree Brackets Fixed a bug so that leg lengths are automatically populated for the listed property and are returned to the automatic lengths if user defined is unchecked e Find FE Tag Fixed a bug so a search can now be performed
311. rake dialog deletion tab Geometry and Load rather than the Geometry Only option then the pressure load is not applied to that panel even though it may lie within the range of sections specified in the Plate group Each method for applying a pressure load is described in more detail below Plate LinPress 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 219 Plate Surface Head Plate Surface Zero Additional Beam Edge Plate LinPress LoadCase v Name General Mass PointForce Pressure Balance Plate LinPress Plate Surface Head Plate Surface Zero Additional Beam Edge F Full Strake Compound v Add Plate Group Module Name Tye D Pressure on Edge 1 N mm 2 Pressure on Ed gt Delete Modify Del Row Close Help The Plate LinPress pressure loading option is that of an actual pressure This pressure can be added to a predefined plate group this will result in only being able to define a constant pressure via the drop down arrow just to the left of the Add Plate Group button or alternatively can be added to a strake If a pressure load is to be applied to panels of the strake the user can define the pressure along the strake edge 1 and strake edge 2 Using this option the pressure can vary linearly across the strake width Plate Surface Head 2009 DRS Defense Solutions LLC Advanced Technology Center 220 MAES
312. rake or compound as the tank boundary by clicking on any part 6 Click inside the main white part of the dialog box and then select the elements that make up the tank boundary faces The Select By Box option can be checked to use a box window to add all the plate elements within that select box Once an element is added to the group right clicking on the element will bring up a menu allowing the user to flip normal side or add all elements with the same property material stiffener layout or type This will apply to all elements in the current view part 7 The Normal of the element can also be flipped by double clicking in the Flip Normal column to change between Yes and No Once the Flip Normal is changed to Yes or No it will remain the same as new elements are added to the definition 8 Select a color from the drop down menu to give the tank a unique color 9 Click the Create button The new tank will appear under the group tab of the parts tree under the Volume folder as the name given in the Groups dialog box 10 Right click the tank name and select Set View Part 11 Select View gt Plate gt Volume Plate Pressure Side from the menu This will show the pressure side of the tank due to its volume contents In order for MAESTRO to treat the tank load properly the tank plate elements should all have their 2009 DRS Defense Solutions LLC Advanced Technology Center 188 MAESTRO 9 0 7 volume press
313. rall Defaults Constraints Structure Groups Module General AEU v Add Constraints LOCAL X Remove Group Constraint STANDARD Min Max STANDARD Constraint Set 00002 yes general group 001 Min Max yes general group 001 Constraint Set 00002 yes general group 001 Constraint Set 00003 yes general group 001 LOCAL yes Acronym Apply Close If you want to create this data yourself you should clear the six lines by highlighting them and clicking on Remove Then recreate them as follows 1 In the first box select Standard Inthe second box select Min Max 3 Click on Add which generates the first line in the List Box saying that Min Max is the first Constraint Set in the Standard Group 4 In the second box select Constraint Set 2 5 Click on Add which generates the second line in the List Box saying that Constraint Set 2 is the second Constraint Set in the Standard Group This completes the Standard Group 6 In the first box select General Group 1 This is the group that was defined using the Groups Dialog Box and it consists of strakes 2 and 3 of module 1 7 In the second box select Min Max 8 Click on Add which generates the third line in the List Box saying that Min Max is the first Constraint Set in General Group 1 2009 DRS Defense Solutions LLC Advanced Technology Center Tutorials 337 9 In the second box select Constraint Set 2 10 Click on Add which generates the fourth line i
314. ransverse gt Torsional Moment command under the the Hull menu is used to display the FE model s transverse torsional moment distribution as shown below MAESTRO also echoes this distribution to the Output window which is found at the bottom of the MAESTRO GUI In conjunction with the View Transverse Torsional Moment command the user can use the Dynamic Query which can be initiated via the t v icon to query the distribution graph To use this functionality the user must select the View Transverse Torsional Moment command toggle the Dynamic Query icon and move the mouse cursor over a particular portion of the graph This will produce a text box with graph data Further the user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph entity of interest Weight Summary The Weight Summary command under the the Hull menu is used to produce weight summary tables in the Output window as shown below 2009 DRS Defense Solutions LLC Advanced Technology Center 94 MAESTRO 9 0 7 o ad D 5 top zal 5 s1 bow a s2 midbody B m1fr25 49 o m2fr49 63 E E s3 stem a aE stss A A A A e e Le BE Parts H Gr pa arts OUPS xxxxxxxxSummary of Module Gross Weight Exclude Volume and Bay Set Weight x xxxxx a WEIGHT 1b XCG in YCG in ZCG in Module Name F 119587 372
315. ration End Moment Corrosion User defined CG Re define constraints Natural freq analysis Delete Modify Help The general tab allows the user to select the particular load options as well as view the status summary of the currently selected load case Depending on which options are checked the load tabs will activate de activate accordingly Mass Tab The Mass tab allows the user to add previously defined groups to the load case definition as well as redefine the values of these groups Properties of masses can be added using six options as volumes as scaled up structural mass as sections as various groups of point masses and as large solid masses whose centroid is at an appreciable distance from the supporting nodes such as main engines and bays of containers For each load case any combination of the previously defined groups Volume Module Section Node and Bay can be chosen and specific properties can be assigned if they differ from the default value MAESTRO will use these values to calculate all of the inertia forces in all members throughout the structure and apply these as loads NOTE In non Sl unit systems that specify densities in force units the masses should be defined in terms of weight for example the fps or ips unit systems use pounds as a weight where mass is specified Therefore when using a unit systems that specifies density in terms of force this can be found in the Units dialog mass s
316. reate a separate fine mesh analysis model of the general group with a 1 to 1 ratio All strake panels frames and girders will be converted to quad and beam elements This model can then be exported to Nastran to analyze with the global response imposed through the use of RSpline elements Internal stiffener layout properties if existing are automatically lumped to the edges of their associated element Either method follows the same general procedure 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 293 1 Create a general group of the elements that will be refined into the fine mesh model 2 Right click on the group name in the parts tree and select refine This will open the Refine dialog box Refine FineMesh Module Name est Join Tolerance 0 003937 in User Defined Module Origin optional in Default C User Defined es Pt cs Analysis Type Top Down C Embedded ALPS HULL C Nastran Map Load Control ji M Map Loads Mesh Controls Minimum length along non stiffened edge O default in Minimum of segments between stiffeners Convert beam frame girder web to 1Quad Convert beam frame girder s flange to Beam v The fine mesh model will be created as a module with the given name either under top if you are using the embedded method or separately for the top down method The join tolerance and user defined module origin can be overwritten if de
317. rent module A set of nodes is created along the line between these two points at the module spacing defined in the Parts dialog This tutorial shows the procedure for creating a set of EndPoints 1 Make sure the appropriate module is set as the current part and launch the EndPoints dialog from the Model gt Nodes gt Create Modify gt EndPoint menu or from the toolbar Reference Points EndPoints Additional Nodes ID v Cartesian Cylindrical X in Y in Z in Reference 0 0 0 TT el Create Modify Delete Close 2 Click the ID button to get the next unique ID for the new EndPoints The Reference and Opposite X values will be automatically filled according to the module location and sections definition in the parts dialog 3 The Y and Z values can be typed in by the user or snapped to a point in the model by clicking in one of the coordinate value boxes and then clicking a point in the model Values can be snapped to other EndPoints Additional Nodes or Construction Markers 4 Click the Create button This same procedure can be repeated for additional EndPoints Toolbar Menu Model gt Nodes gt Create Modify gt Additional Node 2009 DRS Defense Solutions LLC Advanced Technology Center 154 MAESTRO 9 0 7 5 10 Additional nodes allow the user to insert individual nodes into the model in addition to the sets created with EndPoints This tutorial shows the pro
318. retize the design variables i e to convert them to standard sizes During most of the design cycles MAESTRO deliberately treats all design variables including the number of stiffeners as continuous variables in order to avoid the enormous computation and complexity of discrete variable optimization This also has the advantage of allowing the designer to see what the idealized optimum is and thus perhaps obtain new ideas regarding the degree of standardization and commonality or at least be better able to guide and direct the discretization process In the DAT file the input data for discretization consists of a list of available thicknesses the roundoff fractions and the size increments This information is supplied in the DISCRETE data group at the beginning of the optimization data At present the Modeler does not yet have a Dialog Box for the user to enter this data Instead it has just one box for entering a fixed increment in plate thickness and in producing the DAT file it simply adopts the default values for all other items in the discretization data If you want to use other values you must edit the DAT file and type them in Editing the DAT file is similar to editing the OUT file in the Main Menu click on Edit MAESTRO Dat and the Modeler will bring up the DAT file using the Notepad editor The format for typing the discretization data is given in Appendix A taken from the Data Preparation Manual In a DESIGN job for which di
319. rom the display not lying in the specified YZ plane plus the thickness of the slice YZ Slice issues a prompt to specify a point on the desired plane This point may be specified by clicking on a point in the modeling space or entering the coordinates in the form of x y z at the command line The default slice thickness is defined internally in the Modeler as 10 cm Erases everything from the display not lying in the specified ZX plane plus the thickness of the slice ZX Slice issues a prompt to specify a point on the desired plane This point may be specified by clicking on a point in the modeling space or entering the coordinates in the form of x y z at the command line The default slice thickness is defined internally in the Modeler as 10 cm Erases everything from the display not lying in the specified XY plane plus the thickness of the slice XY Slice issues a prompt to specify a point on the desired plane This point may be specified by clicking on a point in the modeling space or entering the coordinates in the form of x y z at the command line The default slice thickness is defined internally in the Modeler as 10 cm Cutting planes can have any arbitrary orientation in space This command places a cutting plane with a user specified orientation The user is prompted to specify a vector normal to the plane a point on the plane and a point on the visible side of the plane These points may be specified by clicking on a
320. rsed area END ENTITY Entity 6 Propeller Sectional Data PROPSECTS Note Indenting is for clarity only not used in actual data file IDF 3 03 or greater SENTITY PROPSECTS VESSEL NAME Identifier for this vessel or job DATA SOURCE Program that wrote the file DATE mm dd yy TIME hh mm ss SUNITS This line must be either SI meters or User Defined If User Defined then the following line s must be specified of user units meter COMMENTS This is a comment about the propeller about to be described Can be any of 79 character lines GEOMETRY rotation Right or Left hand number of blades expanded blade area ratio propeller diameter dim nominal pitch dim 2009 DRS Defense Solutions LLC Advanced Technology Center Appendices 405 hub diameter dim blade thickness ratio may be zero rake at tip positive downstream dim n number of sections type XY Offsets or Camber Thickness section 1 section n where each expanded section format is SECTION section name e g 0 7R radial position dim chord length dim maximum thickness dim location of max thickness from leading edge dim local pitch dim distance of generator line to mid chord positive in the direction of the leading edge dim rake positive downstream dim maximum camber dim location of max camber from leading edge dim j number of radial sections point 1
321. ructural Design Method Trans SNAME 1981 6 Hughes O F A General Method for Computer Aided Optimum Structural Design of Ocean Structures Banda and Kuo eds North Holland Elsevier Amsterdam 1985 pp 13 26 7 Hughes O F Computer Aided Optimum Structrual Design of Tension Leg Platforms International Conference on Computer Aided Design in Marine and Offshore Industries Washington D C 1986 Keramidas and Murthy eds Springer Verdag Berlin 1986 8 Bathe K J Finite Element Procedures in Engineering Analysis Prentice Hall Inc Englewood Cliffs New Jersey 1982 9 Vernon T A Bara B and Hally D A Surface Panel Method for the Calculation of Added Mass Matrices for Finite Element Models Defense Research Establishment Atlantic Technical Memorandum 88 203 February 1988 10 MacNeal R H A Simle Quadrilateral Shell Element Computers and Structures Vol 8 pp 175 183 1978 11 MacNeal R H and Harder R L A Fefined Four Noded Membrane Element with Rotational Degrees of Freedom Computers and Structures Vol 28 Vo 1 pp 75 84 1988 12 American Petroleumm Institute Bulletin on Stability Design of Cylindrical Shells API Bulletin 2U May 1987 13 Computer Science Department University of Basel Switzerland Parallel Sparse Direct Solver PARDISO User Guide Version 3 2 pp 3 14 Intel Intel Math Kernal Library Intel MKL 10 1 In Depth pp 10 15 Richard H MacNeal and
322. ructural adequacy Also this information can be echoed in text format to the output window located at the bottom of the GUI Getting Help Using this help file This help is designed to be used on screen It is extensively cross linked so that you can find more relevant information to any subject from any location If you prefer reading printed manuals a PDF version of the entire help is installed in the Help subdirectory located in the directory where you installed MAESTRO by default C Program Files MAESTRO Help This may be useful as a reference but you will probably find that the active hyperlinks cross references and active index make the on screen electronic version of the help much more useful Getting Started Start by studying the About MAESTRO and General sections Using the help while you re working As far as possible the help is separated by the basic steps of finite element modeling and analysis This makes easier to find the answer to your question based on your stage of the finite element analysis process e To find information on a specific topic navigate to the appropriate FEA step General Geometry Finite Element Modeling Checking The Model Loading The Model Post Processing 2009 DRS Defense Solutions LLC Advanced Technology Center Introduction 21 e When you re frustrated use the Index and Search functions as well as check out the Frequently Asked Questions section Tutorials
323. ry nodal forces and moments applied to simulate the user defined vertical shear force or the vertical shear force calculated by MAESTRO to balance the model The dynamic query t y force and moments at individual nodes icon can be used to query the Horizontal Bending This option will graphically display the boundary nodal forces and moments applied to simulate the user defined horizontal end moments The dynamic query icon can be used to query the force and moments at individual nodes Note this is only applicable if transverse symmetry is not checked in the Job Information dialog Horizontal Shear This option will graphically display the boundary nodal forces and moments applied to simulate the user defined horizontal shear force or the horizontal shear force calculated by MAESTRO to balance the model The dynamic query t 7 icon can be used to query the force and moments at individual nodes Note this is only applicable if transverse symmetry is not checked in the Job Information dialog Torsion This option will graphically display the boundary nodal forces and moments applied to B simulate the user defined torsional moments The dynamic query icon can be used to 2009 DRS Defense Solutions LLC Advanced Technology Center 70 MAESTRO 9 0 7 4 8 query the force and moments at individual nodes Note this is only applicable if transverse symmetry is not checked in the Job Information dial
324. s MPC equation 0 206175 0 308765 0 206175 0 175299 0 308765 0 206175 0 206175 0 19494 0 0117685 0 20965 0 386007 0 17611 0 20965 0 0117685 0 20965 0 386007 0 000163241 0 000379629 0 000311296 0 0124518 0 000770647 0 000311296 0 000379629 0 000311296 0 0124518 0 000199203 0 00996016 0 000199203 0 000796813 00996016 0 000199203 0 000199203 00610254 00488962 9 49073e 006 0 000379629 0 00607407 9 49073e 006 0 00488962 9 49073e 006 0 000379629 oO 1 AOO 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 Frequently Asked Questions 382 MAESTRO 9 0 7 12 12 1 Frequently Asked Questions This section covers some problems that are frequently encountered by users of MAESTRO The questions are organized by category and where necessary links are provided to relevant sections of the help file General Questions e What are the recommended graphics card settings The recommend settings in the View Options dialog are Rendering Options Hardware Z buffer Video Driver OpenGL Driver Driver Options Double Buffering e If the MAESTRO auto recovery functionality fails can still try to recover my model Open the location where the original model was saved You will see a filename mdl and filename bck Change the filename of the bck file and change its extension to mdl Now open the newly named mdi file this is your re
325. s a new Constraint Set number 3 in which there is a constraint that the stiffener spacing must not be less than 12 inches as might be needed to accommodate automatic welding machines The Breadth Between Stiffeners BBS is an alternative design variable to the number of stiffeners STF The following four steps were used to create this Constraint Set If you want to create it yourself then you must first delete it by using the down arrow to select Constraint Set 3 and clicking on Delete Then do the following 1 Click on the ID button to generate a new Constraint Set having the next available ID number 2 Go to the line labeled Breadth Between Stif and toggle double click the Operator until the gt symbol appears Click in the cell under V1 and type in 12 4 Click on Create If you make any subsequent changes be sure to click on Modify before leaving the page Later in the third page of the Dialog Box when we assign the Constraint Sets to Groups we will include Constraint Set 3 in a Group that refers to the strakes for which this constraint is to be imposed These will be strakes 2 and 3 which are the side strakes in the structure 2 7 Using General Groups to Identify Modules and Strakes The Standard Group of constraint sets is a module independent group which serves as a default group for all modules We also need a way of identifying individual modules and 2009 DRS Defense Solutions LLC Advanced Technology Center
326. s or alternatively the user can ask MAESTRO to automatically choose between the two vectors 2009 DRS Defense Solutions LLC Advanced Technology Center 304 MAESTRO 9 0 7 based on the maximum projected area of the element onto the XY or YZ cutting plane This projection of area is illustrated in Figure 7 and Figure 8 for the XY global cutting plane and Figure 9 and Figure 10 for the global XZ cutting plane Y Y 2 Figure 8 Projected Area on XY Cutting Plane Z Figure 7 Element Projected Area on XY Cutting Plane Figure 9 Element Projected Area on XZ Cutting Plane Figure 10 Projected Area on XZ Cutting Plan Since in this example the projected area in the XZ cutting plane is the larger of the two the 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 305 chosen stress vector would lie in the XZ cutting plane as shown in Figure 10 As noted in the beginning the example described above shows how in plane stress vectors are determined and aligned to the Global X axis The user has the ability to also align the in plane stress vectors to the Global Y and Global Z axes in a similar manner The sections below describe the options available for directional stress Global X Global X via XZ XY Cutting Plane This will align the elements in plane stress vector to the global X direction based on largest projected area on the XZ or XY p
327. s the distance between FP and AP LPRC projected chine length Overall longitudinal length of chine projected onto a horizontal plane Longitudinal limit of APB LWL length of waterline Overall longitudinal length of the waterplane RHOW mass density of water Standard ITTC values at 15 deg C 59 deg F are Fresh 1 9384 Ib sec 2 ft 4 101 87 kg sec 2 m 4 specific gravity of 0 9990 Salt 1 9905 Ib sec 2 ft 4 104 61 kg sec 2 m 4 specific gravity of 1 0259 3 5 salinity Note specific gravity uses international convention of distilled water at 3 98 deg C 1 9403 Ib sec 2 ft 4 101 97 kg sec 2 m4 SWH wetted surface of the hull 2009 DRS Defense Solutions LLC Advanced Technology Center 402 MAESTRO 9 0 7 Entire immersed surface of the hull neglecting appendages Large added volumes such as skegs may have a contribution to hull wetted surface and there should be data agreement between SWH and DISV TM draft at midship Molded hull draft on centerline located at MIDP Value reflects the principal hull volume and should not be confused with a keel draft that includes the effect of appendages or skegs TR trim Vessel trim by the stern Equals the draft at AP less the draft at FP XFB longitudinal center of buoyancy from FP Longitudinal distance of the center of buoyancy aft of the FP XFG Longitudinal center of gravity from FP Longitudinal distance of the center
328. scretization is requested it is performed as part of the last design cycle and the subsequent evaluation cycle then provides a check that the resulting scantlings still satisfy all of the constraints The discretization is not simply a rounding up all of the design variables to the next standard size Rather it consists of six cycles which are referred to as rounds in order to distinguish them from design cycles Each round begins with the rounding off up or down according to the roundoff fractions specified by the designer of a further one two or three design variables followed by a full optimization of the remaining free undiscretized variables In this way if a design variables is rounded down the remaining free variables will adjust themselves so as to prevent whatever slight degree of inadequacy 2009 DRS Defense Solutions LLC Advanced Technology Center 348 MAESTRO 9 0 7 might otherwise occur We now want to perform one more cycle of optimization starting with the results of cycle 5 and obtaining discretized results In Job No 2 labelled ex2_no_girder and consisting of cycles 4 and 5 we did not make any changes to the structural model Therefore we have a restart file ex2_no_girder sO1 that is valid and complete and we could now perform a 6 cycle using the same Modeler file ex2_no_girder mdl In the Job Information Dialog Box we would enter 5 in the Restart Cycle box and enter 1 in the Design Cycl
329. se Normal Rotate Local X Create Modify Delete Close 2 Make sure the appropriate module is set as the current part and click the ID button to assign a unique ID to the element 3 Click inside the Node 1 box and then click the four nodes that will define the quad element in the model 4 Select the plate property from the Property drop down menu If the property is not defined click the Property button to define a new plate element property 5 Select the stiffener layout if applicable 6 If a stiffener layout is chosen chose the orientation of the stiffeners in the Direction drop down menu 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 161 Note Edge 1 is defined as the edge between nodes 1 and 2 Edge 2 between nodes 2 and 3 Edge 3 between nodes 3 and 4 and Edge 4 between nodes 4 and 1 7 Check the Wetted box if the element is part of the bottom or side shell 8 Click Create This procedure can be repeated to create additional quad elements Toolbar Menu Model gt Elements gt Create Modify gt Triangle This tutorial shows the procedure for creating an individual triangle element 1 Begin by opening the Finite Element Triangle dialog box using the Model gt Elements gt Create Modify gt Triangle menu the toolbar or clicking the Tri tab in the Finite Element dialog box Finite Elements Springs Rods Beams Triangles
330. se nodes The target values of distributed mass are specified and may differ for each section interval The target values refer only to the modules for which they are defined In the simplest case when each module constitutes a complete transverse section of the structure the target values correspond to the full cross section of the structure or to a half section for a half 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 191 model However if some of the modules are in parallel such as a hull module surmounted by a superstructure module then the target values of distributed mass must be divided and apportioned among those modules In a half model all specified values of mass should be half values A sections group is used to define a non structural mass which is distributed among the sections of a module The additional mass on the module can be either equal for all sections or different for each section Within each section each endpoint generated node carries the same mass 1 Begin by opening the groups dialog box using the Groups gt Section menu option or from the toolbar Volume Plate Module Section Node Bay General Corrosion D g Name v J Module all sections Module Name Section Interval Lengt Mass per Lengt Mass Color Create Del tem 2 Click the ID button to assign a unique ID to the section group 3 Type a descriptive
331. since it was developed in house it can be used to troubleshoot an error if the Sparse solver is not able to solve Whereas an error from the Sparse solver is indescript the Skyline solver will return an error message directing to a specific error in the matrix and an FE tag Eccentric Beam Element This element consists of only the beam itself That is both the area A and the parameter a AE L and the moment of intertia and the parameter f El LS refer to the beam alone and is calculated about the beam s own centroid the centroidal axes being denoted as x y However the element nodes are located not along the beam s centroidal axes but rather at the toe of the web as shown in Fig 8 16 That is the origin of the element axes x y is located at a distance g below the origin of the centroid axes such that y y g Therefore in this type of modeling the plate elements are located at their true position in the plane of the plating However the axial force in the beam continues to be proportional to the change in length of the neutral axis and this is displaced from the element x axis 1 2009 DRS Defense Solutions LLC Advanced Technology Center 230 MAESTRO 9 0 7 Figure 8 16 Eccentric beam element Hybrid Beam Element The element is termed hybrid because the axial stiffness and the bending stiffness are based on different cross sections The axial stiffness parameter is a AE L in which the
332. sired 3 Select the Analysis Type 4 Select whether the element loads from the coarse mesh model should be mapped onto the fine mesh model This would include tank pressure mass etc loads 5 The minimum length along non stiffened edge can be set to control the mesh size 6 Select how the model s web and flange elements should be treated 7 Click OK The fine mesh model is created and the deformation of the global model is prescribed to the fine mesh model using rigid spline elements The following loads are automatically prescribed to the fine mesh model from the coarse mesh model e Immersion 2009 DRS Defense Solutions LLC Advanced Technology Center 294 MAESTRO 9 0 7 8 14 e LinPress e Surface Head e Surface Zero e Point load e Convert mass nodal group into point mass e Convert mass bay group into point mass e Convert mass plate group into point mass The rigid splines create a connection between the coarse mesh nodes and the fine mesh additional nodes For more information on rigid spline elements see the Creating Additional Elements section An embedded fine mesh model will automatically solve by analyzing the coarse mesh model The top down model must be solved after the coarse mesh model is solved by right clicking on the fine mesh module and selecting solve or solving all the fine mesh models at one time by selecting File gt Analysis Evaluation gt Local FEA To view the co
333. so be set in the View Options dialog or from the View Toolbar 2009 DRS Defense Solutions LLC Advanced Technology Center 40 MAESTRO 9 0 7 Set Visibility gt On Off Transparency On Transparency Off This option allows the user to set a module display on or off and transparent or not transparent These options can also be set in the Parts Tree Set Window gt Output Tree v Status Bar This option allows the user to show or hide the parts groups tree the output section and the status bar Element Type This option is the default MAESTRO view where each type of element has a different color In conjunction with the Element Type view the user can dynamically query and element to change it from wetted to unwetted and vice versa reverse the element normal and rotate the local x axis of the element To use this functionality the user must first change to the Element Type view toggle the Dynamic Query icon move the mouse cursor over a particular element right click the mouse and finally select the menu item Wetted Elements This option will change the view to display on the elements that are defined as wetted 2009 DRS Defense Solutions LLC Advanced Technology Center General 41 In conjunction with the Wetted Elements view the user can dynamically query an element to change it from wetted to unwetted and vice versa To use this functionality the us
334. speed cest ut e 228 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 a BB WO N ON OD 10 11 12 13 14 15 16 17 Part IX 1 2 Part XI Importing an Analysis Model nnnnnnnnnnnnnnes 231 Analyzing the Modell ccccsseeeceeesseeeeeenseeeeeeenseeeeeensseeeeeensneeseeenseeeseensaneeeeenseeeeeeensueeeeenseeeeeeeess 235 Natural Frequency Analysis sssnesnnnnennnnnnneennnnneenennnnnnnnnnee 237 Stress ReSUS 50 E S EA Saeed Last so bte a depannage E 240 Rodi Sa i ee ee 240 Bean ses emternenlenenss 241 Bare Plate 25 us danaa daadaa 243 Stiffened Panel 244 Aaly sis ReSUITS 5 2655 ne et ne AAA nn et ne 246 Viewing Stress RangesS ennennnnnnnennnennennnnennenes 250 Viewing Areas of Interest nsssnsernnsnneennsnnnenennsnnnnennnnnnnnns 252 Failure Mode Evaluation nneeeenesensneneenennesnesennne 254 MAESTRO aa eeter anara eae den ete rent ne M mme rene enter 256 Panel Failure Modes items entiere di ee 257 Girder Failure Modes 265 Frame Failure Modes 266 ALPS ULSAP nia vente a eee eed eee a aaria 268 ALPS UD pen 5e ne Ed erate eee nee Oe 269 Running Standalone Evaluation ccssceesscsesseeseeesesseeeseneseesseeseessesseneseeseeeseesseessessenssnseneseeseeesseeseenseaseneneees 278 Post processing Failure Modes ccsscesesesessneeeseeesseeeseneeseeesseeeseneeesneesenesseneeseneenaeeseneeasaeeseneseseeesenee
335. ss menu displays the web thickness of all beam elements in the model This helps the user to identify mistakes in the model 2009 DRS Defense Solutions LLC Advanced Technology Center General 51 In conjunction with the Beam Web thickness view the user can use the Dynamic Query tool which can be initiated via the LM icon to change the thickness in a particular element To use this functionality the user must first change to the Beam Web view toggle the Dynamic Query icon move the mouse cursor over a particular element right click the mouse and finally select the thickness of choice Plate The Plate view under the Thickness menu displays the plate element thickness in the model This helps the user to identify mistakes in the model 2009 DRS Defense Solutions LLC Advanced Technology Center 52 MAESTRO 9 0 7 In conjunction with the Plate thickness view the user can use the Dynamic Query tool which can be initiated via the LM icon to change the thickness in a particular element To use this functionality the user must first change to the Plate view toggle the Dynamic Query icon move the mouse cursor over a particular element right click the mouse and finally select the thickness of choice Composite Layers The Composite Layers view displays the number of layers associated with all composite elements in the model Global Fine Mesh This option will display the m
336. sseeteas 278 Using Evaluation Patches i csctes cade tacas coed a PENA AEE Aiae TARAR A AROEN ETA ASERNE 279 Viewing Stress in a Given Direction 283 Recovering Composite Layer StresSes nennnneennnnenneenss 284 Creating and Analyzing a Fine Mesh Model 286 Contour d o E E cine ech ci ce hia eae eA cel eae kaka del 294 Transparency ViICW ccceseeeeceeeseeeeeeenseeeeeenseeeeeeenseeeseensneeeeeenseeeseeensueeseensaeeeeeenseeeeesenseeeeeenseeeeeeenss 295 ExXporting a Model en cnmrrne tetes ent nt te uent ee anis tete 297 Directional StreSscoaccca baci ees onan Sect EE A dent lue ses M E E T 300 Advanced 312 Batch Processing aroia AENEA AAE AEETI REE E AA AEE 312 PROQKAMIMING PR Re 315 Read Results cotter ne en Aa a venue becuse cuca Sn ee cae es Lee den ot sn de 315 R n MAESTRO Solvers i ciiicccisccscseccskessessoscevencasetceceascouesucseusecensensductheteeccessencsseasvestevsncsecerveouesusesescedsetessaseueeesece 316 Importing Hydro Loads snan detections de concenese cecceetsscoueeeeusuueneevusccuseseyecueesey 316 Tutorials 319 Basic Features s 2c iois s i Seine ee ee tiie tee ee ee Sa a ee ee 319 01 11110741 1011 RE ER Re eip ienien ii 319 Defining the Model ie isiessserennnnnrennennnnnnnneennnnennenennenenensenennnnennnnneneneenenneneensnnnes 319 Optimization Data csceeceeeeeeetnseeeeeneee 321 References and Figures 351 Appendix A iis iiecisedissiaseascedessiestndbeacenanaandsbacesssnoeceios saccevacuasus
337. ssion in Plate Girder Yield Tension in Flange Girder Yield Tension in Plate Frame Yield Compression in Flange Frame Yield Compression in Plate Frame Yield Tension in Flange Frame Yield Tension in Plate Frame Collapse Plastic Hinge 8 9 1 1 Panel Failure Modes MAESTRO s limit states for panels cover 11 different modes of failure The table below provides a summary of these failure modes 2009 DRS Defense Solutions LLC Advanced Technology Center 258 MAESTRO 9 0 7 Panel Failure Modes PCSF Panel Collapse Stiffener Flexure PCCB Panel Collapse Combined Buckling PCMY Panel Collapse Membrane Yield PCSB Panel Collapse Stiffener Buckling PYTF Panel Yield Tension in Flange PYTP Panel Yield Tension in Plate PYCF Panel Yield Compression Flange PYCP Panel Yield Compression Plate PSPBT Panel Serviceability Plate Bending Transverse PSPBL Panel Serviceability Plate Bending Longitudinal PFLB Panel Failure Local Buckling Panel Failure Modes Collapse Collapse limit states are defined when the structure or member has failed in its primary load carrying role Panel Collapse Stiffener Flexure PCSF This collapse occurs due to the axial compression and flexure of the plate stiffener combination Each stiffener is regarded as an isolated beam column with the plating acting as one of the two flanges There are three different types of failure modes depending on the sign of the bending mom
338. sverse Shear Force command the user can use the Dynamic Query which can be initiated via the Lhd icon to query the distribution graph To use this functionality the user must select the View Transverse Shear Force command toggle the Dynamic Query icon and move the mouse cursor over a particular portion of the graph This will produce a text box with graph data Further the user can echo this information to the Output window by double clicking the left mouse button while hovering 2009 DRS Defense Solutions LLC Advanced Technology Center General 93 over the graph entity of interest Bending Moment The View Transverse gt Bending Moment option is used to display the FE Model s transverse bending moment distribution Further MAESTRO echoes this distribution to the Output window which is found at the bottom of the MAESTRO GUI In conjunction with the View Transverse Bending Moment command the user can use the Dynamic Query which can be initiated via the t v icon to query the distribution graph To use this functionality the user must select the View Trasnverse Bending Moment command toggle the Dynamic Query icon and move the mouse cursor over a particular portion of the graph This will produce a text box with graph data Further the user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph entity of interest Torsional Moment The View T
339. t 2 Select File gt Import gt from the menu Choose the file type for the input 3 Select your geometry file from it s saved location and click Open Note MAESTRO reads in IDF format but can also convert and read in DXF and GF files using the File Translator dialog box File Translator Translation Type From DXF to IDF From GF to IDF Unit Coordinate Conversion Scale Factors Coordinate Transform XYZ x x Multiplier 1 Input File Units Millimeters v y Multiplier 1 z Multiplier 1 Input DXF Filename C Documents and Settings jfreimuth Desktop ex Ouput IDF Filename c documents and settings jfreimuth desktop exp me M Read translated IDF file 4 Select the Translation Type and any unit or coordinate conversions MAESTRO can also scale the model in any of the three Cartesian coordinate directions 5 Select the Read translated IDF file option if you would like MAESTRO to automatically load the converted file Click OK 6 A prompt will open asking to insert marks Selecting yes will place a construction marker at any curve end points or intersections Creating EndPoints amp Additonal Nodes Quick Reference Creating EndPoints Creating Additional Nodes 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 153 rose 7 Menu Model gt Nodes gt Create Modify gt EndPoint EndPoints are defined by a Reference and Opposite end of the cur
340. t Visibility Off Right click gt Set Transparency On Right click gt Set Transparency Off 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 applied at the module level or the full model The transparent view will allow all internal structure and external structure to be seen at once desired using the main menu or by right clicking on a part within the Parts Tree and MAESTRO has the ability to toggle a part in a regular or transparent view This view can be The transparency view can be set using the toolbar by clicking either the Set Part Transparent icon a or the Unset Part Transparent icon o and then clicking the part selecting Set Transparency On or Off 296 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 297 8 16 Exporting a Model MAESTRO can easily export a mdl file to a nas wcs or wet To export a model select File gt Export from the main menu and then the type of file to export Ansys Nastran Wetted Cross Section Wetted Surface Ansys Nastran This option will launch the Nastran Ansys Export Options dialog Stiffness Matrix MAESTRO can output the stiffness matrix in Nastran format by clicking the box next to this option A Setting button will appear which can be clicked and a dialog will open to change the material pshell and pbar properties Static Analysis
341. t Force Tab LoadCase Name General Mass PointForce Pressure Balance v Add Total Force ID Module Name Fx N Fy N Fz N Mx N m My N m MZ N m Mass kg Ixx kg m 2 Iyy gt Modify Del Row Close Help The Point Force tab allows previously defined groups or a user selected node to have a force moment or combination of forces and moments applied to it If a group is given a point force or moment the force or moment is evenly distributed to the nodes in the group If there is symmetry of structure a half model and if the current load set is also symmetric then any point loads that lie in the center plane of the structure should be full values The inertia components are defined for the group and are used for dynamic analyses Pressure Tab This tab provides five methods of defining the location and magnitude of pressure loads which are to be applied to the panels quadrilaterals and triangles of this model in the current load case Within each panel all pressure loads are cumulative Thus if two pressure loads of opposite sign are specified for the same panel the final total load is the net value of the two For a panel in a strake pressure is positive when it acts on the side of the plating opposite from the transverse frames If it is desired that the pressure acts on the same side as the frames then the pressure should be made negative If a panel element has been deleted by the St
342. t name rows columns in surface mesh long l trans vert coords of mesh points B row col where col varies fastest long l trans vert coords END ENTITY Entity 3 NURBS Surface Data NURBS Note Indenting is used for clarity only not used in actual file IDF 3 01 or greater 2009 DRS Defense Solutions LLC Advanced Technology Center 396 MAESTRO 9 0 7 SENTITY NURBS VESSEL NAME Identifier for this vessel DATA SOURCE program that wrote the file DATE mm dd yy TIME hh mm ss SUNITS This line must be either SI or User Defined If User Defined then the following line s must be specified of user units meter COORDINATE SYSTEM coordinates of a point one unit forward starboard down coordinate gnomon e g for FAST SHIP 1 1 1 COMMENTS This is a comment about the ship about to be described Can be any of 79 character lines GEOMETRY n number of parts or surfaces part 1 part n where each part is PART 2009 DRS Defense Solutions LLC Advanced Technology Center Appendices 397 part name nonrational or rational basis function in u w directions e g open or periodic order in u w directions integers 1 j rows columns in defining polygon net integers knot vector in u direction floating point knot vector in v direction floating point long l trans vert coords weight of net points B i j where j varies fastest long l
343. t remember these new triangles are based on the properties of the prototype triangle After completing the Quick Creation sequence there are two important things to remember The first is to toggle off the quick creation icon and second the Quick Creation process does not update the ID numbers in the dialog box Therefore if you are going to continue using the dialog box you must close the Finite Element Dialog Box and the reopen it Beam Creation The user must create a prototype beam element in the usual manner for the other elements This will serve to define all of the properties except for the node locations After creating this prototype beam select the Beam option from the drop down menu The user can now single click on the first node in the model that is to become the element node 1 in the new beam and then double click on the second node Repeat this process for as many beam elements as you wish but remember these new beams are based on the prototype beam After completing the Quick Creation sequence there are two important things to remember The first is to toggle off the quick creation icon and second the Quick Creation process does not update the ID numbers in the dialog box Therefore if you are going to continue using the dialog box you must close the Finite Element Dialog Box and the reopen it Rod Creation The user must create a prototype rod element in the usual manner for the other elements This will serve
344. t state becomes the requirement that stiffener buckling must not precede plate buckling A detailed description of this mode of failure can be found in Ref 18 Panel Failure Modes Unservicability Serviceability limit states are defined when the deterioration or loss of other less vital functions have occurred Panel Yield Tension Flange Compression Flange PYTF PYCF This limit state examines the combined axial stress and stiffener bending stress in the stiffener flange The bending stress in the flange is taken at the nodal connection For PYTF the strength ratio is Y E Royre Cia O m Oy where oy is the yield stress of the stiffener Sxia IS the mid X normal stress or mid Y normal depending on the orientation of the stiffeners and o is the bottom X normal or bottom Y normal stress For PYCF the strength ratio is Y 7 Ca On Yp Royer where oy is the yield stress of the plating ia S the mid X normal stress or mid Y normal depending on the orientation of the stiffeners and o is the bottom X normal or bottom Y normal stress 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 263 In both cases y is the combined safety factor for serviceability failure Panel Yield Tension Plate Compression Plate PYTP PYCP The plate flange of the stiffener is investigated in the same manner as the stiffener flange Panel Serviceabi
345. t the same time There is also a new icon to set current part and set view part Background Color The new MAESTRO default background color is light gray with gradient north To change back to a black background or another color open the Preferences dialog from File gt Preferences Capture View A new feature has been added under the File menu which allows the user to copy a screenshot of the modeling space to their clipboard which can then be pasted into another program Importing Legacy Results A new mechanism has been added to facilitate the importing i e opening PLG files of legacy MAESTRO results Hull Menu A newly designed Hull Menu with options to view horizontal and transverse plots 2009 DRS Defense Solutions LLC Advanced Technology Center Latest Updates 11 e Solving Fine Mesh Models Multiple top down Fine Mesh models can be solved at once from the File gt Analysis Evaluation menu or Analysis Evaluation dialog e Groups A new feature has been added within the groups dialog to add additional elements that are similar to an already selected element e Check amp Merge Dialog The functionality found in the Check amp Merge Dialog namely Update FE Tags Free Edges and Evaluation Patches has been moved to the Tools gt Renumber FE Tag View gt Edges gt Free Edges and Model gt Evaluation Patch gt Auto Generate menu items respectively e Model Summary Functionality used to report numbe
346. te Design of Steel Plated Structures Paik and Thayamballi The following are the modes of failure examined by the ALPS ULSAP evaluation method e Overall collapse of plating and stiffeners as a unit e Collapse under predominantly biaxial compression e Beam column type collapse e Local buckling of stiffener web e Tripping of stiffener e Gross 2009 DRS Defense Solutions LLC Advanced Technology Center 20 MAESTRO 9 0 7 3 2 ALPS HULL Strength Assessment Finally the progressive collapse analysis of ships under hull girder loads can be assessed in MAESTRO using the optional ALPS HULL module The theory behind ALPS HULL is presented in Ultimate Limit State Design of Steel Plated Structures Paik and Thayamballi Post processing After the analysis structural response and or structural evaluation MAESTRO provides visualization features that enable you to quickly interpret the results verify loading conditions and record results Deformation plots stress plots contour plots and animations of each loading condition are available in MAESTRO As previously mentioned MAESTRO makes extensive use of dynamic querying not only in the model stage of the FEA process but the post processing stage as well For example while the user is graphically post processing with dynamic query turned on a pop up window displays the exact information that is being used to create the graphics i e stresses deformations st
347. te Warped Quad E Launch Post Processor None C FEMAP Nastran Data File C Documents and Settings My Documents MAESTRO O The procedure for this type of analysis is the same as for a static analysis except there are now more options available Structural Mass Matrix There are two options for dealing with the structural mass matrix MAESTRO can either export the densities and let Nastran calculate the mass the Consistent option or MAESTRO can lump the mass at the nodes and export these values the Lumped option External Shell Added Mass The two options for exporting the external shell added mass are to have MAESTRO write the MFLUID card to be read in Nastran or MAESTRO can use it s own functionality to 2009 DRS Defense Solutions LLC Advanced Technology Center 300 MAESTRO 9 0 7 8 17 calculate the added mass and apply this mass to the nodes of the external shell elements The Setting button is used to change the MFluid card settings default values are used otherwise Internal Tank Mass The two options for exporting the internal tank mass is have MAESTRO write the MFLUID card to be read in Nastran or MAESTRO can lump the mass into the nodes defining the tank skin elements so that the mass and center of gravity of the fluid is matched Wetted Cross Section This option will launch the Export Wetted Cross Section dialog which allows the user to select the location to save the wcs file The n
348. te editor program if the Use Non MAESTRO Editor option is checked Choose Editor Program This option allows the user to select a text editor program to use for nas files outside of MAESTRO Use Non MAESTRO Editor This option allows the user to toggle on or off the option to use a Non MAESTRO editor for Nastran data A check mark will appear next to the option in the menu if a Non MAESTRO editor is to be used otherwise the Nastran data will open in the Output tab View Menu The View menu provides several options for viewing the model that help in the FEA modeling process A brief description of each option is discussed below 2009 DRS Defense Solutions LLC Advanced Technology Center 38 MAESTRO 9 0 7 Undo View Change Pan Rotate Zoom Set View Set View Style Set Visibility Set Window Yv Y v Element Type Wetted Elements By ID gt Groups d Constraints Edges Evaluation Patches Plate Thickness TT Global Fine mesh All Modules Element X Axis amp gt Top Layer Fiber Dir Options Refresh Undo View Change This option will undo the last change to the model view made For example if the model is being viewed in the profile view and is changed to body plan choosing this option will return the view to profile Pan This option allows the user to pan the model with the mouse This can also be done by holding the Shift key and clicking and holding the mouse wheel
349. ted the in plane stress vector will be automatically determined by MAESTRO To illustrate MAESTRO s logic for determining the in plane stress vector let s take the following example of a given element in 3D space Figure 1 below MAESTRO creates two global cutting planes that intersect the centroid of the element The example below illustrates the alignment of the in plane stress vector with the Global X axis therefore the two cutting planes created are in the XY and XZ cutting planes The XY and XZ cutting planes are shown below in Cyan and Green respectively Figure 2 below Y Y Xz X Figure 1 Element in 3D Space Figure 2 Global a a aad XY Cyan amp XZ Z Using the intersection of the element and the global cutting plane an in plane stress vector is created as shown for the global XY cutting plane in Figure 3 and Figure 4 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 303 Z Figure 3 Element amp XY Cutting Plane Intersection Figure 4 In plane Stress Vector A similar process for the global XZ cutting plane results in another in plane stress vector as shown in Figure 5 and Figure 6 Y Y Figure 5 Element amp XZ Cutting Plane Intersection Figure 6 In plane Stress Vector As described above MAESTRO has located two in plane stress vectors The user now has the ability to use the in plane stress vector generated from the XY or YZ cutting plane
350. tended Optimization Output Level ob Cancel Help NOTE After deleting the girders it would have been easier to simply rerun the job from the beginning for the full 5 cycles i e ignore the Restart Cycles box 2009 DRS Defense Solutions LLC Advanced Technology Center 346 MAESTRO 9 0 7 leave it at zero and in the Design Cycles box click the up arrow to obtain the number 5 Then there would be no need to create a new restart file for the first three cycles it would have been created as part of the restart file for the 5 cycle job The only reason for restarting from cycle 3 was to demonstrate how to restart a Job from any cycle rather than starting all over For a full ship model this can save a considerable amount of execution time Before making a restart run the designer can make further changes to the model as long they do not change the number of strakes or the number of girders For example changes could be made to the loads the optimization constraints and the objective function Run the restart job This starts with the results of cycle 3 and produces cycles 4 and 5 You will be asked about overwriting ex2_no_girder DAT That DAT file was made when we repeated the first three cycles We now want to do cycles 4 and 5 and so we do need to update the DAT file Click Yes We will now look through the output of this second job which is the file ex2_no_girder OUT Open the output file by going
351. ter License amp Copyright 411 and Documentation it will notify Licensor in writing that such destruction has taken place and that the SOFTWARE will not be used or reactivated by Customer in the future Customer may terminate this License Agreement at any time by returning all SOFTWARE and Documentation to Licensor or destroying all SOFTWARE and Documentation and notifying Licensor as above Any termination under this provision whether by Licensor or Customer shall be without rebate or any reduction in the amount owed or paid Any cause of action or claim accrued or to accrue because of any breach or default shall survive termination of this License Agreement Articles 2 3 4 5 6 7 12 and 14 shall survive any expiration or termination of this License Agreement 10 TAXES Any prices and fees for SOFTWARE or services exclude any applicable sales use excise value added or other taxes or assessments which are or may hereinafter be levied or imposed by any federal state local or other public taxing authority howsoever designated Any such taxes or assessments except for Licensor income taxes levied or imposed as a result of this License Agreement shall be the Customer s obligation solely and the Customer shall be responsible for all such payments 11 FORCE MAJEURE Except for any payment obligations neither party shall be in default for any delay or failure to perform hereunder due to causes beyond its reasonable c
352. terial Outside Diam Wall Thk in Up Down Create Delete Modify Close 2 Click the ID button to assign a unique ID to the rod element property 3 Give the rod element property a descriptive name 4 Define the rod by its Principal Dimensions Outside Diameter and Wall Thickness or its Integrated Characteristics Section Area and Moment of Inertia 5 Select the material for the rod from the drop down menu 6 Click Create This tutorial shows the procedure for creating a new spring element property 1 Click the Spring tab 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 149 Properties Plate Beam Rod Spring Identification Properties X Spring Constant fo Ibf in Maximum X Travel fo in Y Spring Constant fo Ibf in Maximum Y Travel fo in fo in Z Spring Constant fo Ibffin Maximum Z Travel X Spring Con Y Spring Con Z Spring Con Down Create Delete Modify Close 2 Click the ID button to assign a unique ID to the spring element property 3 Give the spring element property a descriptive name 4 The spring properties are defined by the spring constant in the X Y and Z directions as well as the permissible travel permitted in each direction This travel distance is assumed to be the restriction in stretching and compressing the spring 5 Click Create 5 7 Defining Stiffener Layouts EAG Menu M
353. the Dynamic Query which can be initiated via the ibd icon to query the graph To use this functionality the user must select the View Neutral Axis command toggle the Dynamic Query icon and move the mouse cursor over a particular portion of the graph This will produce a text box with graph data Further the user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph entity of interest 2009 DRS Defense Solutions LLC Advanced Technology Center 86 MAESTRO 9 0 7 Shear Center The View Longitudinal gt Shear Center command under the the Hull menu is used to display the FE model s shear center as shown below In conjunction with the View Shear Center command the user can use the Dynamic Query which can be initiated via the mr icon to query the graph To use this functionality the user must select the View Shear Center command toggle the Dynamic Query icon and move the mouse cursor over a particular portion of the graph This will produce a text box with graph data Further the user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph entity of interest 2009 DRS Defense Solutions LLC Advanced Technology Center General 87 Warping Constant The View Longitudinal gt Warping Constant command under the the Hull menu is used to display the FE model s
354. the steps to analyze a coarse mesh model A model can be analyzed with or without balancing the model first 1 Open the Analyze dialog from the File gt Analysis Evaluation gt Global FEA menu option or from the toolbar 2009 DRS Defense Solutions LLC Advanced Technology Center 236 MAESTRO 9 0 7 Analysis Evaluation Static Analysis Equation Solver Method Sparse Iterative C Skyline Beams Attached to Plating fe Eccentric Beam C Hybrid Beam Stresses amp Reaction Forces M Calculate Stresses M Calculate Reaction Forces Failure Mode Evaluation fe None C MAESTRO C ULSAP Salve All Fine Mesh Models 2 Click the radio button to choose the Equation Solver Method Sparse Iterative Skyline 3 Select the the beam elements should be treated either as Eccentric Beams or Hybrid Beams 4 Check whether to calculate stresses and reaction forces 5 Click the radio button for the type of Failure Mode Evaluation to perform if applicable If evaluation patches have not been created MAESTRO will automatically create the patches during the analysis process 6 MAESTRO can also save the fine mesh models if applicable automatically after solving the global model by checking the box Any errors or issues with each load case will be shown in the output tab otherwise a dialog box will appear stating the analysis is complete 2009 DRS Defense Solutions LLC Advanced Technolo
355. the strake optimizations in whatever sequence of strakes was requested If none was requested as here the strakes are optimized in numerical order The order is only relevant if the LINK option is being used whereby some design variables in some strakes can be required to match or bear a fixed relationship to the already optimized variables in other strakes in a masterslave manner 2 11 Results Of The First Design Cycle If the Job Type data specified the normal level of output as in this example there is no output during the entire strake optimization process When it is finished the results are presented in three tables 2009 DRS Defense Solutions LLC Advanced Technology Center Tutorials 341 1 the final set of active constraints for each strake page 27 2 the new values of the module flexural properties page 28 3 the new values of the design variables for each strake and the corresponding value of the objective function page 29 This information can be very useful since it indicates where the design is heading precisely which constraints are driving it and how much benefit has been achieved This gives the designer some valuable insight and a better grasp of the situation in many ways such as a better appreciation of what is important and what is not In many cases it also gives ideas for improving the design in more general ways such as by adding or deleting members or by changing the
356. ther large complex thin walled structures MAESTRO Requirements e Operating Systems not tested Windows XP 64 bit 2000 e Operating Systems not supported Windows ME 98 95 NT e Mac The Intel Mac with Bootcamp or Parallels has not been tested e Microsoft NET Framework 2 0 e Valid license without this MAESTRO will operate in the demonstration mode e Installation of Sentinel System Driver and Sentinel Protection Server 7 5 0 required for proper hardware lock functionality e PARALLEL PORT SECURITY DEVICES ARE NO LONGER SUPPORTED PLEASE CONTACT THE ATC TO ORDER A USB SECURITY DEVICE Version 9 0 7 New and Enhanced Features e Layout Organization Many of the menu items and icons have been reorganized renamed or changed to provide the user with a more consistent and effortless experience Please see the documentation for a complete description of menus and icons e RBE3 A new element RBE3 has been added to MAESTRO The intended use of the RBE3 is to transmit forces and moments from a primary node to one or more secondary nodes without adding any stiffness to the structure e Transverse Bending Moments A newly designed Hull Menu includes options to view transverse plots of bending moments This is especially useful when designing multi hulls e Transparency This new feature allows the user to choose to set a module or substructure as transparent for easier viewing of the model e Groups Creation Operation New functionalit
357. ting Horizontally in a Free Surface JSR Vol 3 Number 4 March 1960 3 L Landweber and Matilde Macagno Added Mass of Two Dimensional Form Oscillating in a Free Surface JSR Vol 1 Number 3 Nov 1957 2009 DRS Defense Solutions LLC Advanced Technology Center Verification and Validation 373 11 4 Bracket Bracket Element 1 Background MAESTRO bracket element 1s used for a simplified coarse mesh analysis It can be attached to an end of a beam element to get stress reduction The technique involves separate modeling of the axial and bending stiffness The axial stiffness is modeled by a super element method It is assembled with tapered axial elements for the bracketed portion and a standard axial element for the rest of the beam Internal nodes are eliminated by condensation of the stiffness matrix Tt Cross Section Area A2 Cross Section Area A1 wa woe J E The bending stiffness of the assembly is obtained by matrix transformation A portion of the bracket is modeled as a rigid link element and the remaining part of the beam is modeled as a regular beam element 2009 DRS Defense Solutions LLC Advanced Technology Center 374 MAESTRO 9 0 7 Bending Stress Location Rigid Element RBE2 2009 DRS Defense Solutions LLC Advanced Technology Center Verification and Validation 2 Verification e Axial
358. ting Plane User Defined Cutting Plane C Specify In plane Vectors pp ke e of pP Cancel The stress direction can be either applied to the Full Model or the Current View Part by clicking the appropriate radio button in the Define Stress Direction dialog Stress direction settings can be set for multiple view parts and will be applied when viewing the entire model or multiple view parts As an example the next two figures show a module with the elements stress vector first aligned in the global X direction Figure 11 and the second aligned in the Global Z direction Figure 12 Figure 11 shows the panel element s all have their local x axis orientated in the Global X direction whereas Figure 12 shows the panel element s all have their local x axis orientated in the Global Z direction In this example we would expect the sigma x stress of Figure 11 to be equal to sigma y which is now in the direction of the Global X axis of Figure 12 to be equal and vice versa 2009 DRS Defense Solutions LLC Advanced Technology Center 308 MAESTRO 9 0 7 5 64E 003 4 12E 003 top s2 midbody m1 fr 25 49 strake 16 Quad Sec 1 1E 003 Thickness 0 5 in FeTag 2128 lAngle 0 00 Stresses Mid Ibf in 2 SigX 9 2000E 002 SigY 6 6591E 000 Tau 613 962 SigVM 1 4040E 003 Corner Stress 3E 002 VM1 1 6070E 003 I ou VM2 1 7398E 003 VM3 1 2876E 003 pese VM4 1 1156E 003 poms 5E 003 9E 003
359. tion of the nodes are presented in Table 1 2009 DRS Defense Solutions LLC Advanced Technology Center 360 MAESTRO 9 0 7 Table 1 Patch Test Model Node Locations BCs Theoretica Theoretic MAESTRO MSC Nastr Input Data an for Windows 0 00012 U 6 0e5 patchy f06 Surface Stress s 0 533 2009 DRS Defense Solutions LLC Advanced Technology Center Verification and Validation 361 11 1 2 BCs Theoretica Theoretic MAESTRO MSC Nastr Input Data l al an for Strain Stress Windows V3 0 Constant Twist 0 5e Surface q 0 000121q 0 00012 patchws m Biaxial Bending My 3 33e 08 Table 2 Patch Test MAESTRO Quad Element vs MSC Nastran for Windows V3 0 QuadR Element Results Cantilever Beam The second test is a cantilever beam modeled with six trapezoidal or parallelogram shell elements The dimensions and the material properties are given in Figure 1 Three loads are applied at the free end of the beam a unit force in the Y direction in the plane of the element a unit force in the Z direction out of plane and a unit twisting moment The in plane force causes in plane shear The out of plane force causes shell bending The critical part of this test is the in plane shear The MSC Nastran QUAD4 element completely failed the in plane test because of shear locking The MAESTRO element is only 1 2 different from the theoretical value For the out of p
360. tions LLC Advanced Technology Center 170 MAESTRO 9 0 7 boxes the user can delete specific elements by selecting them with the mouse or by ID or delete all of one element type at once This tutorial shows the different ways an element or elements can be deleted 1 An element can be deleted using the Model gt Elements gt Delete gt menu the Tools gt Deletions gt Select Tools gt Deletions gt All Visible gt or from the toolbar Parts gt Mirror gt Materials Properties ULSAP Parameters Nodes d Create Modiy Stiffener Layout Select Evaluation Patch gt Al Visible gt Beams Bracket Define Constraints Compounds Balance Quads Rods Summary RSpines Springs Strakes Triangles Deletion Jv Full Strake Cmpd V Strake Compound Box Jv RSpline V Tri V Quad V Beam V Rod V Spring V Bracket Module Name New Module Return Item to Model Delete 2 The Model menu allows the user to select the type of element to be deleted A specific 2009 DRS Defense Solutions LLC Advanced Technology Center Geometry Finite Element Modeling 171 element can be selected using the mouse or by the element ID 3 The Deletion dialog box allows the user to select multiple elements to delete by clicking on them with the mouse The check boxes at the top of the screen serve as a filter for which types of elements may be deleted Checking Box all
361. tors are 1 25 for serviceability limit states and 1 50 for ultimate or collapse limit states These values are specified in the criteria page 2 of the output 10 2 2 Optimization Data OPTIMIZATION DATA This chapter shows how to use the Groups Dialog Box and the Optimization Dialog Box to define the data needed for optimization 2 1 Optimization Initial Settings Job Information Dialog Box Before beginning any optimization task you should always perform a MAESTRO structural analysis on the entire model and be sure to correct all errors and serious inadequacies After 2009 DRS Defense Solutions LLC Advanced Technology Center 322 MAESTRO 9 0 7 an analysis job in which there are no serious inadequacies you should open the Job Information Dialog Box from File gt Analysis Evaluation gt Legacy Version of MAESTRO gt Job Information MAESTRO Job Information General Structure Origin amp Balancing Units Criteria Comments Job Title ELA ERE AAE CIES Job Type Analysis Optimization F Save Deflections Design Cycles ee Deflections Available ee 0 Preliminary Cycles M Final Evaluation Strake Opt Cycles 0 Jv Save Scantlings F Scantlings Available Output Level oltre ExtendedLevelforLast 0 cycles C Extended Optimization Output Level fo The General Page in the Job Info Dialog Box is the only page that needs to be altered to initiate the optimizer T
362. tput window which is found at the bottom of the MAESTRO GUI In conjunction with the View Longitudinal Bending Moment command the user can use the Dynamic Query which can be initiated via the LM icon to query the distribution graph To use this functionality the user must select the View Bending Moment command toggle the Dynamic Query icon and move the mouse cursor over a particular portion of the graph This will produce a text box with graph data Further the user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph entity of interest 2009 DRS Defense Solutions LLC Advanced Technology Center 78 MAESTRO 9 0 7 0 00E 000 2 47E 006 7 40E 006 9 87E 006 1 23E 007 1 48E 007 1 73E 007 1 97E 007 2 22E 007 2 A7E 007 2 71E 007 2 96E 007 3 21E 007 3 46E 007 3 70E 007 3 95E 007 Torsional Moment The View Longitudinal gt Torsional Moment command under the the Hull menu is used to display the FE model s longitudinal torsional moment distribution as shown below MAESTRO also echoes this distribution to the Output window which is found at the bottom of the MAESTRO GUI In conjunction with the View Longitudinal Torsional Moment command the user can use the Dynamic Query which can be initiated via the LM icon to query the distribution graph To use this functionality the user must select the
363. tructure strakes 2 and 3 They will disappear to confirm that they have been selected 4 Normally at this point you would click on Create and then on Close and you would have created a second General Group consisting of strakes 2 and 3 of module 1 But since we already have General Group we don t want this second group so click only on Close 5 Re open the Optimization Dialog Box 2 8 Optimization Dialog Box Page 3 Creating Groups Of Constraint Sets As noted earlier optimization is performed separately for each module The optimization data is specified in two Groups 1 one Standard Group a module independent group of Min Max constraints and other Constraint Sets which serve as default Constraint Sets for all modules 2009 DRS Defense Solutions LLC Advanced Technology Center 336 MAESTRO 9 0 7 2 any number of module specific General Groups containing Constraint Sets which can selectively override the default Constraint Sets and which can also include other types of Constraint Sets that are not in the Standard Group The association of Groups and Constraint Sets is done in the third page of the Optimization Dialog Box with Structure as its tab In the first box you select which type of group Standard or General and in the second box you select one by one which Constraint Sets are to be in that group The next figure shows the completed Dialog Box Group Optimization Settings Ove
364. u Model gt Parts gt Create Modify A MAESTRO model is made up of parts or more specifically substructures and modules In the model hierarchy modules make up substructures which make up the full model Before you begin modeling it is a good idea to first review your structural drawings and plan out your Substructure and Module breakdown This tutorial shows the procedure for creating a substructure and an accompanying module 1 Begin by opening the Substructures and Modules dialog box from the Model gt Parts gt Create Modify menu or from the toolbar Substructures and Modules General Location Sections Default Values Part Type C Module fe Substructure PartName top Create Modify Delete 2 Select top from the local parts tree the radio button should be selected for Substructure under Part Type 3 In the Part Name box type a forward slash after top and give a descriptive name for the substructure click Create Note if you click the next to top the substructure just created will be shown along with any other substructures created 4 In the Location tab set the Origin Location and Rotation Angles for the substructure and click Modify Note the origin location of the substructures is relative to the top origin location which by default is 0 0 0 2009 DRS Defense Solutions LLC Advanced Technology Center 138 MAESTRO 9 0 7 Substructures and Modules Genera
365. uced failure at Panel Edges PCSB Stiffener induced failure tripping PCWB Panel Collapse Web Buckling PYM Yield in Mid Plane PYF Yield in Flange PYP Yield in Plate Mimimum Value Beam BCT Tripping BYC Gross Yielding BCWB Web Buckling BCC Collapse Beam Column FCPH Collapse Plastic Hinge Minimum Value All Negative Positive MAESTRO s limit states cover failure modes associated with Panels Girders and Frames The table below provides a summary of the 23 failure modes automatically evaluated using the MAESTRO criteria 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 257 Panel Failure Modes PCSF PCCB PCMY PCSB PYTF PYTP PYCF PYCP PSPBT PSPBL PFLB Girder Failure Modes GCT GCCF GCCP GYCF GYCP GYTF GYTP Frame Failure Modes FYCF FYCP FYTF FYTP FCPH Panel Collapse Stiffener Flexure Panel Collapse Combined Buckling Panel Collapse Membrane Yield Panel Collapse Stiffener Buckling Panel Yield Tension in Flange Panel Yield Tension in Plate Panel Yield Compression Flange Panel Yield Compression Plate Panel Serviceability Plate Bending Transverse Panel Serviceability Plate Bending Longitudinal Panel Failure Local Buckling Girder Collapse Tripping Girder Collapse Compression in Flange Girder Collapse Compression in Plate Girder Yield Compression in Flange Girder Yield Compre
366. ults defines only the default min max constraints and these always constitute Constraint Set 1 The rest of the constraints are defined in the second page labeled Constraints The following figure shows the second page with Constraint Set 2 selected in the ID box and after clicking on the Girder tab Each new Constraint Set is created by clicking the ID button and then clicking on Create Then you go to the subpages Plate Girder Frame Other and define the constraints that make up that Constraint Set As you define them you should click on Modify As a minimum you must click on Modify before leaving a subpage or your definitions will be lost Group Optimization Settings Overall Defaults Constraints Structure ID 00002 Name Constraint Set 00002 v Create Delete Modify Plate Girder Frame Stiffener Other Limit State Variable Operator Web Thickness in min max Web Height in min max Flange Thickness in min max Flange Width in min max HGW TGW lt HGW HFW gt BGF TGF min max BGF HGW min max BFF HGW min max TGW TGF min max TGW TPL lt TGW TFW min max The constraints of Constraint Set 2 all impose limits on the proportions of individual members and on the relative sizes and thicknesses between members in order to ensure a balanced and buildable structure Most of the constraints are direct proportions with the left hand side being a simple rati
367. umber 2009 DRS Defense Solutions LLC Advanced Technology Center 224 MAESTRO 9 0 7 7 4 8 Balance Tab LoadCase loo1 Name D General Mass Point Force Pressure Balance Current or initial Imersion Wave Values Units in degree v Sinusoidal V F K Effect Emergence 586 in HeelA Pitch A 0 361 Wave L 0 in Amplitude 0 in PhaseA 0 Heading Center of Flotation Default C Specify Modify Close Help The balance tab of the Loads dialog is used to define a stillwater immersion condition or wave condition if the load is defined as a floating structure The first check box can be clicked to cycle through No Wave Sinusoidal or Trochoidal MAESTRO will automatically calculate and apply the Froude Krylov forces if desired by clicking the check box F K Effect The trochoidal wave profile is calculated from the following equations k L n sin W 2 lt l n LES 2 The first line of inputs defines the models emergence heel angle and pitch angle The second line of inputs defines the wave length amplitude phase angle and heading Note all angles are defined in degrees The phase angle is MAESTRO is defined as follows Assume the ship is stationary For a positive phase angle shift the wave moves forward compared to the original position 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 225 The Center of Flotati
368. umber of parts or bodies part 1 part n where each part format is PART part name m number of curves curve curve m where each curve format is CURVE 2009 DRS Defense Solutions LLC Advanced Technology Center 394 MAESTRO 9 0 7 curve name Curve type station buttock waterline cant incline diagonal diagonal general plane three d j integer number of points on curve point 1 point j where points are coordinate triplets long l trans vert breakpoint indicator unknown fair knuckle for example 10 15 3 25 1 50 fair END ENTITY Entity 2 Surface Mesh Data MESH Note Indenting is used for clarity only does not exist in actual file IDF 3 01 or greater SENTITY MESH VESSEL NAME Identifier for this vessel DATA SOURCE program that wrote the file DATE mm dd yy TIME hh mm ss SUNITS This line must be either SI or User Defined 2009 DRS Defense Solutions LLC Advanced Technology Center Appendices 395 If User Defined then the following line s must be specified of user units meter COORDINATE SYSTEM coordinates of a point one unit forward starboard down coordinate gnomon e g for FAST SHIP 1 1 1 COMMENTS This is a comment about the ship about to be described Can be any of 79 character lines COORDINATE GEOMETRY n number of parts or surfaces part 1 part n where each part is PART par
369. ume plate module section and node There is a very close relationship between groups and MAESTRO loading as will be seen in later sections The loads in MAESTRO are particularly unique in that they are ship based An example of ship based loading is tank loading hydrostatic loading both still water and wave induced bending moments deck loading and externally imposed bending moments to name a few A few of these are shown below Checking Your Model At each stage of the FEA process you receive graphical verification of your progress MAESTRO provides tools for checking your model before and after analysis which gives you confidence that you have correctly modeled the structure MAESTRO makes extensive use of dynamic querying which allows the user to make changes graphically while checking the model Dynamic query is a powerful tool that is used in all phases of the FEA process The dynamic query functionality is intended to be used in conjunction with particular MAESTRO menus e g the View Loads Hull and Results menus In combination with these particular menus the user can make changes on the fly while modeling i e thickness material pressure sides etc In addition to graphically presenting model properties such as element thickness plate beam web and beam flange positive pressure sides and beam properties to name a few MAESTRO provides built in integrity checks for element aspect ratios disconnected elements war
370. urchased this optional module A complete description of the theoretical basis for the ALPS ULSAP module can be found in Reference 2 ALPS ULSAP s limit states cover failure modes associated with Panels Girders and Frames The table below provides a summary of the 13 failure modes automatically evaluated using the ALPS ULSAP criteria Panel Failure Modes PCPM Panel Collapse Plate Induced Failure in Midspan PCCB Panel Collapse Overall Grillage Collapse PCPE Panel Collapse Plate Induced Failure at Panel Edges PCSB Panel Collapse Stiffener Induced Failure Tripping PCWB Panel Collapse Web Buckling PYM Panel Yield Mid plane PYF Panel Yield Stiffener Flange PYP Panel Yield Plate Girder Failure Modes BCT Beam Collapse Tripping BYC Beam Gross Yielding 2009 DRS Defense Solutions LLC Advanced Technology Center Analyzing and Post Processing 269 8 9 3 BCWB Beam Collapse Web Buckling BCC Beam Collapse Beam column Frame Failure Modes BCT Beam Collapse Tripping BYC Beam Gross Yielding BCWB Beam Collapse Web Buckling BCC Beam Collapse Beam column FCPH Frame Collapse Plastic Hinge ALPS HULL The following capability is an optional MAESTRO module Run Fast Lock if you are not certain have purchased this optional module Introduction Creating an ALPS HULL Model Analysis Setup Post processing NOTE Sample ALPS HULL analysis models ALPSHULL_0O mdl ALPSHULL_1 mdl and ALPSHULL_2
371. ure side on the inside of the tank 12 While still in the Volume Plate Pressure Side view the dynamic query can be used to highlight an element and right click and select Flip Pressure Side to change the pressure side It is helpful to use the shrink elements view El to verify the pink pressure side is on the inside of the tank Plate Group A plate group is a group of panel elements that can be used to apply a mass or pressure load to 1 Begin by opening the groups dialog box using the Groups gt Plate menu option or from the toolbar Groups Volume Plate Module Section Node Bay General Corrosion Name Centerline Group F Full Strake Full Compound SelectByBox Mass 0 kg Module Name N Create Del Item Close 2 Click the ID button to assign a unique ID to the plate group 3 Type a descriptive name into the Name box 4 Check the Centerline Group if the plate group spans the centerline of a half model This will automatically combine the mirrored group into one single group if the model is mirrored 5 Checking the Full Strake Full Compound box will include the entire strake or compound as the part of the plate group by clicking on any part of the strake or compound panels 6 Click inside the main white part of the dialog box and then select the elements that make up the tank boundary faces The Select By Box option can be checked to use a box window to add all the plate elements within
372. ve commands before each auto backup and click OK to save Model Recovery In the event that MAESTRO freezes or the program crashes you can easily recover your model by selecting File gt Recover Model from the menu You will be prompted whether you are sure you want to recover the model and clicking Yes will automatically open the last created auto backup model The filename bck file is still created and saved in the location of the mdl file and can be loaded as described in the FAQ sections as needed Cutting Planes The cutting plane functionality can be found under the Tools gt Cutting Planes gt menu XY Plane YZ Plane ZX Plane XY Slice YZ Slice ZX Slice Specify Delete Cutting planes are planes in space which delineate visible and invisible regions of space A user can insert a cutting plane into the model and specify which side is visible and which is invisible This can be very useful at times such as when wishing to view only the interior of a full hull model By placing a longitudinal cutting plane at the origin and hiding the port side the interior of the starboard model is made visible The user can create cutting planes aligned with any of the principal axes or define a cutting plane with arbitrary orientation In addition the user can specify a cutting slice in which two closely spaced cutting planes are placed in the model with their visible side being the region between them As with all of the View commands
373. ve crest In the figure xc 1 2 j Phase angle Moves a wave crest along the x axis away from the origin xc I 360 In the figure j 180 which places a trough at the origin q The angle between structural coordinate and wave coordinate using the right hand rule To calculate the wave height in a ship structural location x z the structural coordinates should be transformed to the wave coordinates Rotation about y axis 2009 DRS Defense Solutions LLC Advanced Technology Center 204 MAESTRO 9 0 7 x xX cos q z sin q h x sin q z cos q Figure 1 Balanced model Heading 0 Figure 2 Un balanced Model Heading 60 Figure 3 Balanced Model Heading 60 2009 DRS Defense Solutions LLC Advanced Technology Center Loading The Model 205 Figure 4 Balanced Model Rotate Module 60 degrees Heading 60 Equivalent to Figure 1 Figure 5 Un Balanced Model Rotate Module 60 degrees Heading 0 Equivalent to Figure 2 Figure 6 Balanced Model Rotate Module 60 degrees Heading 0 Equivalent to Figure 3 These models balance wave 60 mdl and balance wave rotate 60 mdl can be found in the Models and Samples folder of the MAESTRO installation directory 2009 DRS Defense Solutions LLC Advanced Technology Center 206 MAESTRO 9 0 7 7 4 Defining Loads Toolbar Menu Loads gt Create Modify
374. warping properties as shown below In conjunction with the View Longitudinal Warping Constant command the user can use the Dynamic Query which can be initiated via the LM icon to query the distribution graph To use this functionality the user must select the View Warping Constant command toggle the Dynamic Query icon and move the mouse cursor over a particular portion of the graph This will produce a text box with graph data Further the user can echo this information to the Output window by double clicking the left mouse button while hovering over the graph entity of interest 2009 DRS Defense Solutions LLC Advanced Technology Center 88 MAESTRO 9 0 7 010 3 58E 010 3 31E 010 3 03E 010 2 76E 010 2 48E 010 2 20E 010 1 93E 010 1 65E 010 7 1 38E 010 M 1 10 010 8 27E 009 5 51E 009 2 76E 009 0 00E 000 Torsional Rigidity The View Longitudinal gt Torsional Rigidity command under the the Hull menu is used to display the FE model s torsional rigidity properties as shown below In conjunction with the View Longitudinal Torsional Rigidity command the user can use the Dynamic Query which can be initiated via the me icon to query the distribution graph To use this functionality the user must select the View Longitudinal Torsional Rigidity command toggle the Dynamic Query icon and move the mouse cursor over a particular portio
375. where points are ordered triplets of XY chord position ordinate suction side ordinate press side dim or CT chord position ordinate of camber thickness normal to camber line dim point j END ENTITY Comments These files may contain any number of these entities However when writing to files entities are typically appended to existing files Therefore only the last found entity is typically used when reading entities from files Example of PROPSECTS entity in units of meters SD IDF 3 03 2009 DRS Defense Solutions LLC Advanced Technology Center 406 MAESTRO 9 0 7 SENTITY PROPSECTS VESSEL NAME Sample propeller DATA SOURCE PropCad 2 00 DATE 03 25 97 TIME 08 22 46 SUNITS SI COMMENTS Example of the PROPSECTS entity GEOMETRY Right 4 0 65 1 0 0 9 0 18 0 0702704 O 10 XY Offsets SECTION 0 2R 0 1 0 253418 0 0406 0 0794288 0 72 0 233917 0 0140541 0 0203 0 0794288 15 0 0 0 0142046 0 0142046 0 00633546 0 0219650 0 00923921 2009 DRS Defense Solutions LLC Advanced Technology Center Appendices 0 0126709 0 0256052 0 00684665 0 228076 0 0102679 0 0 0 240747 0 00608771 0 0 0 253418 0 00182631 0 0 SECTION 0 3R 0 4R END ENTITY 407 2009 DRS Defense Solutions LLC Advanced Technology Center MAESTRO 9 0 7 License amp Copyright License amp Copyright 409
376. with the Theoretical Solution 11 1 7 Hemispherical Shell The final test is the hemispherical shell problem This test gives an opportunity to study the solution accuracy of a doubly curved shell The geometric size of the hemispherical shell and the material properties are given in Figure 1 The results are listed in the table below Figure 1 Sphere8 Model Transverse Symmetry Radius 10 0 thickness 0 04 E 6 825e07 v 0 3 2009 DRS Defense Solutions LLC Advanced Technology Center 368 MAESTRO 9 0 7 Figure 2 Sphere8 Boundary Conditions MAESTRO Theoretical Error Input Data Displacemen Displacemen Files t t Refer to Unit Forces sphere8 mdl Figure 2 jin Symmetric y _ 0 090 v 0 094 4 3 sphere8a mod P i sphere8a f06 sphere8a nas Refer to Unit Forces sphere8 mdl Figure 2 jin symmetric 40 090 v 0 094 4 3 P 1 P 2 2009 DRS Defense Solutions LLC Advanced Technology Center Verification and Validation 369 11 2 Rod The rod test is a rod modeled with two solid rod elements of different cross sections The rod is fixed at node 1 The model and node locations are presented in Figure 1 and Table 1 The rod model is applied a vertical compressive force of 1 000 psi at node 8 1 000 psi Node 3 Element 2 A 15ir Node 2 Element 1 A 2in Node 1 Figure 1 Rod Test E 1 0e07 psi The MAESTRO calculated axial stresses re
377. y has been added to allow a user to create a new group from existing groups using the Group Operation dialog Also a new feature has been added within the groups dialog to add additional elements that are similar to an 2009 DRS Defense Solutions LLC Advanced Technology Center 10 MAESTRO 9 0 7 already selected element Combined these features provide the user with a more robust way to create groups Wetted Group To assist in exporting wetted elements to FEMAP new functionality in the Groups menu was added that will automatically create a general group of wetted elements Select by Box To expedite the selection of elements a select by box capability has been added Directional Stress new feature has been added which allows the user to align all element local stress vectors to a global direction This functionality will enable the presentation of stress in a uniform manner to the analyst can better assess the stress patch in a given direction Export Stiffness Matrix MAESTRO can now export the stiffness matrix in Nastran format through the export Nastran options This feature will allow advanced users to process analysis runs in Nastran by using the MAESTRO generated stiffness matrix Batch Execution MAESTRO has the ability to perform batch processing which allows the user to sequentially solve any number of models each of which may have any number of load cases without having to manually launch each
378. y to aid in reference point creation MAESTRO is unique in how these three dimensional nodes are created and manipulated throughout the modeling process therefore it is useful to discuss the hierarchy of the MAESTRO structural model Z MODULE ELEMENTS SUBSTRUCTURE A collection of Modules In the design of large structures it is usually advisable to divide the task into a few distinct subtasks in order to maintain a good overview and control of the design Most large structures can be reduced to several levels of component structures for which the design and analysis is relatively independent Such a structure can best be modeled by subdividing it into a hierarchy of parts down to the module level and then constructing each module using a three dimensional mesh of nodes and appropriate groupings of finite elements As shown above the MAESTRO structural modeling is organized in four levels members elements strakes group of elements modules and substructures Additionally all appropriate materials and section properties can be created with MAESTRO Many types of constraints and loading conditions can be applied to represent the design environment You can apply loads and constraints directly on finite element entities nodes or elements or indirectly through groups MAESTRO groups typically used in load creation 2009 DRS Defense Solutions LLC Advanced Technology Center 18 MAESTRO 9 0 7 are vol
379. ycle showing that all but two constraints are satisfied The table on page 51 shows that they are PYCF in strakes 1 and 4 and that the adequacy parameter is very small being only 0 012 This result verifes that the girders were indeed not needed Up to five modules can be optimized at once but because a typical module is in itself a rather large structure with many design variables and involving a large amount of information it is recommended that only one or two modules be optimized at one 2009 DRS Defense Solutions LLC Advanced Technology Center Tutorials 347 time Once a module has been sufficiently optimized usually in a series of runs each having any number of design cycles and restarting from the results of any previous cycle two final steps are needed 1 the General Group for that module should be removed from the List Box on the Structure page of the Optimization Dialog Box 2 the final scantlings should be copied from the restart file of that module using a text editor as explained in the next section and pasted into the job data Gobname DAT in place of the original scantlings The optimization process is then repeated for another one or two modules again involving a series of runs 2 16 Job No 3 Restart Cycle 6 Discretize At End From the plots of Figure 1 it can be seen that at this point end of cycle 5 the optimization process is close to convergence and hence it is time to disc
380. ystem that is modeled with finite elements and subjected to given loads MAESTRO accomplishes this objective through a single Windows based graphical user interface that completely encompasses the structural modeling preprocessing the ship based loading the finite element analysis the limit state evaluation and the post processing Design System The MAESTRO Design System has four main capabilities overall or global stress analysis structural adequacy limit state evaluation structural design optimization and fine mesh local stress analysis The MAESTRO Design System is comprised of eight principal modules listed below e Modeling Analysis Evaluation e Finemesh Analysis e Eigenvalue Solver Natural Frequency e Optimization e ALPS ULSAP e ALPS HULL e Nastran Translator e ANSYS Translator Modeling Analysis Evaluation This module includes the graphical modeler for developing MAESTRO structural models and full post processing capability This includes full model viewing capability and generation of loads for input to the MAESTRO Analysis Evaluation Solver Post processing includes such features as graphical display of loads deflections stresses and failure evaluation results from the MAESTRO Analysis Solver The two central operations of MAESTRO analysis and evaluation are also performed by this module This module completes a finite element analysis and structural integrity evaluation failure modes and other limit st

MAESTRO Manual - Design Systems & Technologies

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MAESTRO Manual - Design Systems &amp; Technologies

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MAESTRO Manual - Design Systems & Technologies