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ESABASE2

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1. 45 Debris result editor 3D Results Orbital Point context menu 47 Debris result editor 3D Results Coordinate Systems context menu 48 Debris result editor 3D Results Element Chart 49 Debris result editor ADResults nennen 50 Debris result editor 2D Results options ccccecceeeeceeeeeeeeeeeeeseeesaneeseeess 51 Debris result editor 2D Results reporting rrrrrrnrrrrnnrrvnnnrrrnnrernnnennnnrnnnnen 53 Debris result editor 2D results listings rrrrrnnnnrennnnnvvnnnrrvennnrrennnerennnnrennn 54 Debris result editor 2D Results notes 55 ESABASE2 Debris Date Software User Manual Revision Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc State etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig 2009 09 28 Final draft Page 9 55 giele ail 1 Introduction ESABASE2 is a software application and framework for space environment analyses which play a vital role in spacecraft mission planning Currently 2009 it encompasses Debris meteoroid 1 Atmosphere ionosphere 7 Contamination outgassing 5 6 and Sunlight 8 analyses with this it complements other aspects of mission planning like thermal or power generator design The application grew from ESABASE2 Debris an application for space debris and micro meteoroid impact and damage analysis which in turn is based on the original ESABASE Debris software 4 develop
2. e Shielding Parameters Choose shield thickness and density and spacing in case of double walls e Failure and Damage Equation Choose the exact damage equation Depends on the Ground Test choice made above e nput Parameters Impact angle density velocity and diameter can be specified either as single values or as arrays of values Each variable has three parameters the minimum value the maximum value and the number of steps For single ESABASE2 Debris Date 2009 09 28 Software User Manual Revision Reference R077 232rep 01 00 Software User Manual Solver Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 33 55 taya shots only the minimum parameter is used For tabled data when the variable is used as x axis or y curve parameter all three parameters are used e Visualisation Choose the axis on the result graph Unlike the normal Debris analyses the ground test can be performed directly within the Debris input editor for this purpose press the Run button Afterwards the Graph and Table buttons at the bottom right are enabled leading to the popup windows illustrated in the screenshot below BER BER velocity km s Density g cm 3 0 0 1 399999976158142 1 5 0 15865212678909302 1 1 399999976158142 0 1384488344192505 1 399999976158142 0 12456725537776947 1 399999976158142 0 11426488310098648 0 0 1 399999976158142 0 106222003698349 9 99999970909292 1
3. HI SS z llZl EEE DEE EE EN RM mum 1 ESABASE2 Debris Software User Contract No Title ESA Technical Officer Prime Contractor Authors Date Reference Revision Status Confidentiality etamax space GmbH Richard Wagner Str 1 D 38106 Braunschweig Germany Tel 49 0 531 3802 404 Fax 49 0 531 3802 401 email esabase2 etamax de http www etamax de Manual 16852 02 NL JA PC Version of DEBRIS Impact Analysis Tool G Drolshagen J Sorensen etamax space GmbH K Ruhl K Bunte 2009 09 28 RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc 1 0 Final draft etamax space GmbH etauE SB Table of Contents Document lt de 11 d Le BE 3 l Release Note CHR 3 IEEE FOT IST OT Rm 3 VPN cmm 3 VE eng IER TT M 4 VON EE 6 VI NNN 7 NN re 8 no OID ME 10 2 DS 11 2 1 EE ee ER 11 2 2 DENN 14 221 De btris Mal Tan EE 14 222 Debris Ground Test Tod near 33 2 2 3 Debris Non Geometric Analysis Tab 35 gt MEI NATI CETT TUE 38 2 3 1 Geometric Debris Analveis naww munu wuniw wizi wizi uzinzi 38 2 3 2 Non geometric Debris Analys 42 2 4 DNM 44 2AT DIR 44 242 DEN 50 2A 3 NNSA GS a 54 20 Le 55 Revision 1 0 Software User Manual State Final draft Reference R077 232rep 01 00 Software User Manual Solver Debris doc Page 2 55 etamax space GmbH Richard Wagner Stra
4. Different 2D graphs of the debris results can be shown for the entire spacecraft geome try using the 2D Charts tab as described in the next section 2 4 2 However it is also possible to show graphs of only one element Shift Leftclick an element of the S C geometry then open the context menu and select Element Chart The following figure shows the resulting small popup window Chart for element_1 i Chart for element_1 Result Set Result Set WAN dee 0 rd EI Export Image KS Factor edt npe E Total Impact Fluence 1 m 2 vs orbital points for Crater Flux year Total Impact Flux 1 m 2 year 0 0009 element 1 Total Impact Fluence 1 m 2 m U Total Failure Flux 1 m2 year e Total Failure Fluence m 2 E 0 0008 0 0007 2 0 0006 E 0 0005 LL 0 0004 0 0003 D 0 0002 S 0 0001 o 9 0000 00 05 10 15 20 25 30 35 40 Orbital Points Figure 2 35 Debris result editor 3D Results Element Chart From the Result Set combo box select a variable the appropriate graph for the given element will be displayed as shown on the right These are the same values that are colour coded in the element in the 3D view You also have the possibility to adjust the appearance of the graph via the Options button or a context menu opening on rightclicking and to export the image as PNG or JPG via the Export Image button s sections 2 4 2 1and 2 4 2 2 for details ESABASE2 Debris Date 2009 09 28
5. Page 10 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig taya 2 Debris Solver After we have specified mission and spacecraft geometry 1 the next step is to perform Space environment analyses with these One of the available solvers ESABASE2 Debris performs debris and meteoroid analyses within the framework Four space debris models NASA90 16 ORDEM2000 15 MASTER 2001 11 and MASTER 2005 19 as well as three meteoroid models Gr n 14 Divine Staubach 13 18 and MEM 20 are currently available for flux and damage analysis For detailed information on the technical background of the space debris and micro meteoroid simulation please refer to the ESABASE2 Debris technical description 2 This debris solver chapter is structured as follows e Debris Geometry Explains debris specific additions to a S C geometry e Debris Input Describes the input parameters for Debris and meteoroid analyses e Debris Analysis How to perform an analysis e Debris Results How to interpret the analysis results 2 1 Debris Geometry The geometry editor defines a spacecraft geometry for all solvers available within the ESABASE2 framework 1 including Debris Solver specific geometry parameters are de fined using special pages in the shape wizard A dedicated Debris page is shown for each shape allowing you to define the shielding configuration of any shape both primary and secondary shielding Classic su
6. mz wyear fo m mz year 1 1 04 45 93 0 1089E 02 O 6397E 03 0 1355E 02 O 7914E 03 0 1583E z 0 4476E 00 0 1 35 22 36 0 88134E 01 0 7237E 03 0 18508E 02 1031E 03 O 2475E 0O2 O 2721E 00 0 3 0 04 72 34 0 3559E 01 0 1574E 05 0 53864E 00 0 3071E 04 0 6142E 04 0 2645E 04 D 4 1 53 26 50 0 8634E 01 0 5044E 03 0O Z042ZE 02 1165E 3 O 2795E 02 0 2656E 00 0 0 11 53 09 0 9242E 01 0 4545E 05 0 1456E 01 0 5360E 04 0 1003E 03 D 27778E 03 0 5 0 11 54 11 O 9214E 01 O 4590E 05 0 1469E 01 0 8494E 04 O 1019E 05 0 31596 03 D E s T E Motes Listings 3D Results 20 Results Figure 2 39 Debris result editor 2D results listings In the result log you can see the different LIS files just select the appropriate LIS entry in the combo box For Debris Meteoroid Deb Met you can jump to orbital point bookmarks using the second combo box The following LIS files are available e Crater vs Crater size e Deb Met Debris Meteoroid e Failures vs Ballistic Limit e Kinematic e Orbit Detailed information about the contents of the listing files can be found in the original ESABASE user manual 4 Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc Page 54 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig taya Please note The listing files are foremost saved as data nodes in the debris result file A
7. 2009 09 28 ESABASE2 Debris Software User Manual State Final draft Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc Page 18 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig giele ail MASTER 2001 covers the entire altitude range from LEO to GEO 150 km to 37000 km Within the given altitude range there are no restrictions concerning the target orbit so that highly eccentric orbits such as GTO can be analysed The MASTER population snapshots are available from year 1980 to 2020 Consequently historic missions e g LDEF and future missions can be analysed using realistic popula tion snapshots For the future evolution of the space debris environment the following assumptions have been applied e continuation of space activity launches explosions solid rocket motor firings at the same rate as in the recent past e no new satellite constellations deployed e no implementation of debris mitigation measures This corresponds to the MASTER 2001 future reference scenario ESABASE2 Debris Date 2009 09 28 Software User Manual Revision Reference R077 232rep 01 00 Software User Manual Solver Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 19 55 giele ail 2 2 1 1 2 Debris model MASTER 2005 MASTER 2005 19 is ESA s meteoroid and space debris reference model and the succes sor of MASTER 2001 see previous subsubsect
8. 38106 Braunschweig Page 37 55 giele ail 2 3 Debris Analysis With both debris information within the spacecraft geometry and global debris input parameters specified the time has come to perform a debris analysis There are two type of analysis runs e Geometric Analysis This is what you would normally expect A mission and a spacecraft geometry are sent to orbit propagation and debris analysis e Non geometric Analysis Subtracts the S C geometry from the analysis instead taking a simple plate 2 3 1 Geometric Debris Analysis In the toolbar at the top of the application window locate the Run button depicted in the following figure Press the small down arrow at the right of the button and a context menu will appear 2 ESABASE File Edit Window Help S 2 Reset perspective Lcd Run geometric Debris Analysis Run nan geametric Debris Analysis Figure 2 25 Geometric Debris analysis Run button Whenever you click directly on the Run button instead of the down arrow to the right the last selected run type will be repeated Choose the first entry Run geometric Debris Analysis A wizard as illustrated by the following screenshot will appear Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference R077 232rep 01 00 Software User Manual Solver Debris doc Page 38 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Ge
9. Notes Listings 3D Results 2D Results Figure 2 37 Debris result editor 2D Results options You can customize the following chart properties e x y axis o Label Text Changes the text of the axis label o Grid Displays horizontal vertical dashed lines o Label font Label font size Label font style Changes the appearance of the axis label o Maximum Minimum The value range that this chart shows ESABASE2 Debris Date 2009 09 28 Software User Manual Revision Reference R077 232rep 01 00 Software User Manual Solver Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 51 55 etayuE ail o Number format The format of the number labels e g the number of decimal places can be specified o Number scaling Choose between linear or logarithmic scale e Title o Graph title The title text above the chart o Title visible Show or hide the title text o Title Font Title Font Size Title Font Style The appearance of the title text e legend o Legend Show or hide the legend o Legend Font Legend Font Size Legend Font Style The appearance of the legend e Background The background color of the chart e Box Shows or hides the box around the graph e Axis and label colour The colour of the axis lines and the labels e Major tick labels Shows or hides number labels at the major ticks e Minor tick marks Display small ticks between the major ticks e Ratio
10. depicted above Note that the correct pointing e g solar panel aligned towards the Sun can only be shown at the orbital points not for the whole mission or orbital arc etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 47 55 giele ail 2 4 1 3 Coordinate Systems To visualise the coordinate system you used in the geometry editor change the coordi nate system by opening the context menu and navigating to Coordinate Systems as shown in the following figure E gt Landsat _debris result 2009 07 06 16 41 06 Bean t Bs SEN Orbital Point k Coordinate Systems no coordinates global coordinate System centered default Notes Listings 3D Results 20 Results Figure 2 34 Debris result editor 3D Results Coordinate Systems context menu You can choose among the following coordinate system settings e No coordinates Note that pointing vectors will also be deactivated e Global coordinate system centred Shows the xyz axis for the entire system e Global coordinate system in the corner Same as before but in the corner of the system not centred e Global and local coordinate systems Shows xyz axis for each object Detailed but probably slightly irritating for complex S C geometries un f gt ha Na M 1 NN CA d pe vm r Ar A C ance LU Z3ZfCD U U DI VW A Use Nal la Page 48 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig 2 4 1 4 Element Chart
11. 399999976158142 0 19693270325660706 9 99999970909292 1 399999976158142 0 16253291070461273 9 99999970909292 1 399999976158142 0 14183542132377625 Ground Test NASA ISS BLE E 0 225 9 99999970909292 1 399999976158142 0 12761428952217102 9 99999970909292 1 399999976158142 0 11705990135669708 0 200 9 99999970909292 1 399999976158142 0 10882028937339783 E 19 99999941818584 1 399999976158142 0 21206402778625488 E 19 99999941818584 1 399999976158142 0 17502112686634064 G 19 99999941818584 1 399999976158142 0 15273334085941315 o 19 99999941818584 1 399999976158142 0 13741952180862427 2 19 99999941818584 1 399999976158142 0 12605419754981995 9 19 99999941818584 1 399999976158142 0 11718149483203888 5 0 125 30 000000834826 1 399999976158142 0 24123288691043854 30 000000834826 1 399999976158142 0 19909483194351196 30 000000834826 1 399999976158142 0 173741415143013 E 30 000000834826 1 399999976158142 0 1563212275505066 0 075 30 000000834826 1 399999976158142 0 1433926373720169 30 000000834826 39 99999883637 168 39 99999883637 168 39 99999883637 168 39 99999883637 168 39 99999883637168 39 99999883637 168 49 999996837917 49 999996837917 49 999996837917 49 000004277017 5 10 15 20 25 30 35 40 Velocity km s Figure 2 21 Debris input editor Ground Test tab Run Graph and table show the same results Date 2009 09 28 Revision 1 0 State Final draft Page 34 55 1 39999997615
12. 7 Meteoroid model MEM MEM 20 is a meteoroid model developed by the University of Western Ontario Can ada Upon pressing Edit a dialog with the MEM input parameters opens as shown in the figure below reteoroid Model MEM Options Constant meteoroid density gfcn3 2 5 Figure 2 12 Debris input editor main tab Model Selection MEM MEM has no options by itself using a constant meteoroid density of 1 g cm The option available here is used to convert mass to diameter for damage computation We pro pose to always use 1 g cm Please note that the default 2 5 g cm is fitting only for the other meteroid models all models use the same parameter within the data model this is the reason that the de fault in the GUI cannot be 1 g cm MEM is a parametric model of the spatial distribution of sporadic meteoroids The pri mary source is short period comets with aphelia less than 7 AU The model also consid ers the contributions from long period comets to the sporadic meteor complex and in cludes the effects of the gravitational shielding and focussing of the planets ESABASE2 Debris Date 2009 09 28 Software User Manual Revision Reference R077 232rep 01 00 Software User Manual Solver Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 25 55 giele ail 2 2 1 1 8 Jenniskens Stream Model The above meteoroid models are describing the background meteoroid flu
13. Geometry Adv Hole Cutoff angle 90 Use User Subroutine Debris Ground Test Non Geometric Analysis Figure 2 3 Debris input editor main tab At the bottom of the editor you can see the Debris Ground Test and Non Geometric Analysis tabs This subsection is concerned with the main Debris tab In the following the four sections of the main tab will be explained ESABASE2 Debris Date 2009 09 28 Software User Manual Revision Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 15 55 giele ail 2 2 1 1 Model selection Your first decision is which debris and meteoroid models you want to use The follow ing figure shows the model selection block within the Debris main tab Model Selection Analvsis Type debris and meteoroid analysis Iv Debris Model MASTER 2005 se Edit Meteoroid Model Divine Staubach ve L Streams Alpha Beta Separation Apex Enhancement Figure 2 4 Debris input editor main tab Model Selection As a starting point to the Debris analysis you have the choice between debris or mete oroid analyses or both see first combo box Analysis Type Depending on your choice the Debris Model or Meteoroid Model coboboxes will be enabled or disabled ESABASE2 Debris provides four Debris models MASTER 2001 MASTER 2005 ORDEM 2000 NASA90 and three meteoroid models
14. Gr n Divine Staubach MEM Most of the models accept detailed input parameters Press the Edit button to the right of the model combo boxes Additional parameters Streams Alpha Beta Separation and Apex Enhancement are shown below they are valid only for some models Details are given in the sections 2 2 1 1 8 2 2 1 1 9 and 2 2 1 1 10 In the following the available models will be described together with their associated parameters This description is necessarily short a full description can be found in the ESABASE2 Debris Technical Description 2 Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference R077 232rep 01 00 Software User Manual Solver Debris doc Page 16 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig 2 2 1 1 1 Debris model MASTER 2001 MASTER 2001 11 is the 2001 version of ESA s meteoroid and space debris reference model it is the forerunner of MASTER 2005 see next subsubsection When you click on the Edit button a dialog with MASTER 2001 input parameters will open as shown in the following figure Debris Model MASTER 2001 Options Debris density Far constant density gl cm 3 2 8 Launch and mission rel objects Fragments historic population only Mak droplets SRM slag particles SRM Al205 dust historic population only Paint Flakes historic population only Ejecka historic population only Collision Fragments Futur
15. LE COMOVA 1 1 10 Software User Manual ESTEC Contract No 12867 98 NL PA HTS AG and ONERA October 2006 Borde J Sabbathier G de Development of an Improved Atomic Oxygen Analy sis Tool Software User Manual S413 NT 19 94 Issue 2 ESTEC Contract 9558 91 NL JG Matra Marconi Space Toulouse France May 1994 ESABASE Sunlight Application Manual ESABASE SUN UM 072 Issue 2 Rel 2 1 ESTEC Mathematics amp Software Division Noordwijk The Netherlands Septem ber 1994 Bendisch J K D Bunte S Hauptmann H Krag R Walker P Wegener and C Wiedemann Upgrade of the ESA MASTER Space Debris and Meteoroid Envi ronment Model Final Report ESA ESOC Contract 14710 00 D HK Sep 2002 Bunte K D ESABASE Debris Release 3 Technical Description ESA ESTEC Con tract 15206 01 NL ND Upgrade of ESABASE Debris etamax space Sep 2002 Bunte K D ESABASE Debris Release 3 Software User Manual R033 r020 ESA ESTEC Contract 15206 01 NL ND etamax space Sep 2002 Cour Palais B G Meteoroid Environment Model 1969 NASA SP 8013 NASA JSC Houston TX 1969 Divine N Five Populations of Interplanetary Meteoroids Journal of Geophysical Re search Vol 98 No E9 pp 17029 17048 September 25 1993 Gr n E H A Zook H Fechtig R H Giese Collisional Balance of the Meteoritic Complex Icarus 62 pp 244 277 1985 Liou J C M J Matney P D Anz Meador D Kessler M Jansen J R Theall The New NASA Orbital Debris
16. Size Boundaries Size Boundaries Lower particle diameter 0 0010 EE Upper particle diameter 100 0 cm Min crater diameter 0 0010 cm Min eject Fragments 0 0010 cm Figure 2 16 Debris input editor main tab Size Boundaries At the top the minimum and maximum particle size limits can be input as mass g or diameter cm The conversion between mass and diameter assumes spherical particles At the bottom the minimum crater diameter and ejecta fragment size are defined in cm Below these size limits crater or ejecta fragment are not further considered in the analysis ESABASE2 Debris Date 2009 09 28 Software User Manual Revision Reference R077 232rep 01 00 Software User Manual Solver Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 29 55 giele ail 2 2 1 3 Ray Tracing Ray tracing is the primary technique in ESABASE2 to determine whether Debris or Me teoroids hit the spacecraft geometry at a specific orbital point Below you can see a screenshot of the Ray Tracing section in the main tab Ray Tracing Primary rays 100 Secondary rays O Secondary rav jump 1 Figure 2 17 Debris input editor main tab Ray Tracing The Primary rays parameter governs the number of primary rays to be fired per ele ment For ESABASE geometric models at least 250 rays per element are recommended for non geometric analyses 1000 rays In the middle the Seconda
17. Software User Manual Revision Reference R077 232rep 01 00 Software User Manual Solver Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 49 55 giele ail 2 4 2 2D Results Complementing the 3D Results tab described above charts can show different flux distributions in the 2D Results tab An example is shown in the following figure ES Landsat _debris result 2009 07 06 16 41 06 E3 m E MASTER 2005 flux vs velocity orbital point 01 Graph GIN si Flux 1 m 2 yr r2 DJ I LP c weil ze p 00 25 50 74 100 195 150 175 200 225 950 275 300 325 350 375 400 Velocity km s Notes Listings 3D Results 2D Results Figure 2 36 Debris result editor 2D Results In the combo box on the top left you can select the chart you want to see Which charts are available depends on the debris meteoroid model used for the analysis as shown in the following table Debris meteor Flux distributions NASA90 F f d valid for all orbital points MASTER 2001 F f d F f azimuth F f elevation F f velocity for each orbital point MASTER 2005 F f d F f azimuth F f elevation F f velocity for each orbital point ORDEM2000 F f d F f azimuth for each orbital point Gr n F f m valid for all orbital points Divine Staubach F f d F f azim
18. Software User Manual Revision Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 41 55 giele ail 2 3 2 Non geometric Debris Analysis The non geometric analysis uses a simple plate instead of a full spacecraft geometry it is therefore considerably faster As in the geometric debris analysis locate the Run but ton and this time choose Run non geometric Debris Analysis The following figure shows the Run wizard for the non geometric debris analysis GI Non Geometric Debris Analysis Non Geometric Debris Analysis Please choose the input File Far the analysis Project debris testing Debris test ure 5 O6iMeo05 05 Mission test urlte 5 081155 Report options Complete listing of all Figure 2 29 Non geometric Debris analysis Run wizard Compared to the geometric Debris analysis this wizard is considerably simpler The spacecraft geometry input file is omitted and all options have been removed only the report options remain No output file needs to be specified since the result listings are displayed in the Result Log section of the Debris input editor s Non Geometric Analysis tab The content of the listings is stored within the debris input file Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference R077 232rep 01 00 Software User Manual Solver Debris doc
19. StraBe 1 38106 Braunschweig Page 27 55 giele ail 2 2 1 1 10 Apex Enhancement As a modification to the Gr n model the Apex Enhancement describes the meteoroid flux enhancement caused by the earth s motion on its orbit around the sun similar to the enhanced flux a spacecraft experiences in velocity direction If you press Edit a dialog shows the Apex Enhancement input parameters shown in the figure below Apex Enhancement Options RF antapex to apex Flux ratio 2 0 Dy velocity ratio 0 36 Figure 2 15 Debris input editor main tab Model Selection Apex Enhancement Two parameters can be used to describe the ratio of flux and velocities between apex front and antapex back directions see 10 for more details e R antapex to apex flux ratio default 2 0 e D velocity ratio default 0 36 As with Alpha Beta Separation we do not recommend using other values than the de fault values for this model unless you have in depth knowledge in astrophysics Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc Page 28 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig giele ail The figure below shows the Size Boundaries section of the main tab in the Debris input editor In this section you specify limits on the type of Debris or Meteoroids to be used in the analysis 2 2 1 2
20. draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 21 55 giele ail 2 2 1 1 4 Debris model ORDEM 2000 ORDEM2000 15 is a debris model developed by NASA it is the successor of NASA96 which in turn followed NASA90 The model describes the orbital debris environment in the low earth orbit region between 200 km and 2000 km altitude The only user editable input parameter is the assumed debris material density default 2 8 g cm gt as shown in the figure below Debris Model ORDEMZOO0 Options Debris density For constant density gfem 3 2 9 SSC Figure 2 9 Debris input editor main tab model selection ORDEM 2000 ORDEM 2000 is appropriate for engineering solutions requiring knowledge and esti mates of the orbital debris environment debris spatial density flux etc The model includes a large set of observational data both in situ and ground based covering the object size range from 10 um to 10 m The analytical technique uses a maximum likelihood estimator to convert observations into debris population probability distribution functions these functions then form the basis of the debris populations A finite element model processes the debris populations to form the debris environment Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc Page 22 55 etamax space GmbH Richard Wagner S
21. editor contains four major blocks for specifying geo metrical analysis input parameters e Model selection Allows you to choose among debris and meteoroid models and to edit dedicated model parameters e Size boundaries Limits on the type of debris or meteoroids to be considered in the analysis e Ray tracing Defines the accuracy of ray tracing results e Damage Model Defines failure and damage equations for the Debris analysis e User Subroutine How to define your own damage equation in a Fortran library Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc Page 14 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig taya The figure below shows the ESABASE2 Debris main tab within the Debris input editor Model Selection Size Boundaries Analysis Type debris analysis Lower particle diameter 0 0010 Debris Model MASTER 2001 Upper particle diameter 100 0 Meteoroid Model Min crater diameter 0 0010 st Min eject Fragments 0 0010 reams Alpha Beta Separation Apex Enhancement Ray Tracing Primary rays 100 Secondary rays 0 Secondary ray jump Damage Model Failure Equation Damage Equation O Single wall Thick Plate Crater Size Thick Plate Multi wall ESA Triple Q Clear Hole Maiden 5 Use Geometry Advanded Hole Aluminium Use User Subroutine Use
22. export the results Export to ZIP File will save all files First Export geometry File Export mission File Export debris File Export result File Target directory For export Comment that will be included in Ehe Filename cubesat Figure 2 27 Geometric Debris analysis Run dialog export page Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc Page 40 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig giele ail The debris result file will be saved into your workspace This page allows you to addi tionally export the input and result files to a ZIP file suitable for transmission via email or other means Press the Finish button to launch the Debris analysis A progress bar will appear and keep you updated about the current state of the appli cation Depending on the number of elements in the S C geometry and depending on the number of orbital points an analysis might take a long time i e several hours Progress Information Running MASTER 2005 Figure 2 28 Geometric Debris analysis Progress bar After the run a debris result file will be created in your workspace and it will be auto matically opened If you are interested in its contents skip to section 2 4 otherwise the following subsection will explain the non geometric debris analysis ESABASE2 Debris Date 2009 09 28
23. plate normal can be defined o The azimuth angle is the angle with respect to the velocity direction 0 deg corresponds to the ram direction positive towards right o The zenith angle is the angle to the space zenith direction 0 deg corre sponds to the space direction In both cases the area of the plate can be defined Normally the default 1 m is used but a specific area can be specified instead e g in case of a detector or other special surface 2 2 3 3 Failure and Damage Equation Selection The failure and damage equations are the same as for the normal geometric analysis please refer to subsection 2 2 1 4 2 2 3 4 Result Log The results of a non geometrical analysis are displayed in the bottom part of the Debris input editor You can select between four different sets of results e hits vs crater size e debris and meteoroid flux and damage results e failures vs ballistic limit e orbit propagation results All results will be presented in textual form ASCII files The results listings are also available in the ListingFiles folder of the corresponding pro ject directory The names of the listing files are composed from the string NonGeom the analysis date and time and the type of listing result set ESABASE2 Debris Date 2009 09 28 Software User Manual Revision Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1
24. 11 km s and 72 km s ESABASE2 Debris Date 2009 09 28 Software User Manual Revision Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 23 55 giele ail 2 2 1 1 6 UMeteoroid model Divine Staubach Divine Staubach 13 18 is a meteoroid model which is also part of the MASTER 2005 model When you press the Edit button a dialog shows the the Divine Staubach input parameters depicted in the screenshot below Meteoroid Model Divine Staubach Options Constant meteoroid density g cm gt 3 2 5 Figure 2 11 Debris input editor main tab Model Selection Divine Staubach The only parameter is the material density of meteoroids It is assumed to be constant Divine Staubach is based on the size and orbital element distributions of five meteoroid subpopulations and thus provides directional information in the same way as the MASTER 2005 debris model Please note Since the Divine Staubach meteoroid model is implemented in the MASTER Standard application one MASTER 2005 run covers both debris and meteoroid flux de termination if the corresponding switches are set Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc Page 24 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig 2 2 1 1
25. 8142 1 399999976158142 1 399999976158142 1 399999976158142 1 399999976158142 1 399999976158142 1 399999976158142 1 399999976158142 1 399999976158142 1 399999976158142 1 2000000761529147 0 13329951465129852 0 292778342962265 0 24163644015789032 0 21086564660072327 0 1897231936454773 0 1740320771932602 0 16178229451179504 0 3861951231956482 0 31873536109924316 0 27814653515815735 N FEN ER1ATFIAE l ESABASE2 Debris Software User Manual Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig taya The non geometric analysis uses a simplified spacecraft geometry A pointed or ran domly tumbling plate This mode is used to check an analysis environment consisting of the orbit specification the environment models and the damage assessment parame ters 2 2 3 Debris Non Geometric Analysis Tab Using this mode is recommended for large spacecraft models with many elements in order to iron out input errors without running a time consuming full analysis The ray tracing scheme is the same for both geometric and non geometric analyses The following figure shows the Non Geometric Analysis tab in the Debris input editor Af cubesat debris 3 E J Non geometrical Analysis Orientation and Area Shielding Type Single wall v Randomly Tumbling Thickness 0 1 cm Density 2 73 g cm 3 Azimuth Angle 0 0 deg Z
26. Engineering Model ORDEM2000 NASA TP 2002 210780 NASA May 2002 2009 09 28 ESABASE2 Debris 1 0 Software User Manual Final draft Reference R077 232rep 01 00 Software User Manual Solver Debris doc etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig taya 16 Kessler D J R C Reynolds P D Anz Meador Orbital Debris Environment for Spacecraft Designed to Operate in Low Earth Orbit NASA TM 100471 NASA 1989 17 Kessler D J J Zhang M J Matney P Eichler R C Reynolds A Computer based Orbital Debris Environment Model for Spacecraft Design and Observations in Low Earth Orbit NASA TM 104825 NASA 1996 18 Staubach P Numerische Modellierung von Mikrometeoriden und ihre Bedeu tung fur interplanetare Raumsonden und geozentrische Satelliten Theses at the University of Heidelberg April 1996 19 S Stabroth P Wegener H Klinkrad MASTER 2005 Software User Manual MO5 MAS SUM 2006 20 McNamara H et al METEOROID ENGINEERING MODEL MEM A meteoroid model for the inner solar system 21 PROTECTION MANUAL Version 3 3 Inter Agency Space Debris Coordination Committee IADC 04 03 Revision April 04 2004 22 SWENET ESA s Space Weather European Network since 2004 http www esa spaceweather net swenet ESABASE2 Debris Date 2009 09 28 Software User Manual Revision 1 0 Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc State Final draft etamax space GmbH Richar
27. Page 42 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig giele ail The screenshot below shows the debris input editor supplied with results from a non geometrical debris analysis Result Log LISTINGDEBMET EI SEDATE TATE STATE AAA TATA AAT er AAA TAA ESABASEZ Debris rel 2 0 ESTEC etamax space 2008 09 18 Current run Debris only non geometrical analysis Date 06 JUL 2009 Time 25 04 41 SETTER Fr Fr H Debris Ground Test Non Geometric Analysis Figure 2 30 Non geometric Debris analysis results In the Result Log section the combo box toggles between the output files while the text area below shows the content of the selected file Here the Debris Meteoroid list ing LISTINGDEBMET is shown ESABASE2 Debris Date 2009 09 28 Software User Manual Revision Reference R077 232rep 01 00 Software User Manual Solver Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 43 55 giele ail 2 4 Debris Results A geometric Debris analysis produces a debris result file which is interpreted by the De bris result editor The editor contains the following functionalities e 3D Results Shows the spacecraft geometry overlaid with the impact flux or other output parameters e 2D Results Graphs with different data about flux distributions at the orbital points as well as avera
28. Set a fixed aspect ratio e Auto scaling Re scales the chart e Graph Type Choose between line bar and scatter chart e Series num o Linecolour Linewidth Color and width of the line of this data series o Stroke Type of the line of this data series e Range Set the X and Y range that the chart covers 2 4 2 2 2D Charts Image Export Pressing the Export Image button opens a file dialog asking for a location to save to PNG and JPG format are possible The size of the image is the same as it is currently shown resize the application window to get other image sizes Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference R077 232rep 01 00 Software User Manual Solver Debris doc Page 52 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig 2 4 2 3 2D Charts Show Report The chart can be embedded into a print ready report press the Show Report button to invoke it After a dialog asking for a comment line has been confirmed a report as shown in the following figure will appear in a popup window E EsabaseZ Debris Report Print Preview Report Export View Help 5 gt AR 1004 v E ESABASE2 Debris MASTER 2005 flux vs velocity orbital point 01 User Text by Kal Ruhl Table Graph Attributes Attribute Name Velocity km s Flux 1i4m 2 yr Scaling LINE AR LINE AR Minimum 0 0 0 0 Maximum 41 7375 7 986395 1056213379 Figure Chart 2D MASTER 2005 flu
29. Use Geometry adv Hole Cutoff angle 90 0 Use User Subroutine Figure 2 18 Debris input editor main tab Damage Model The following convention is used in the software for single wall surfaces the single wall ballistic limit equation is used for the failure assessment the crater size equation for the damage assessment cratered area for multiple wall surfaces the multiple wall ballistic limit equation is used for the failure assessment the clear hole equation for the damage assessment The damage equations of the ESABASE2 Debris analysis tool are defined in a parametric form with editable parameters constants and exponents For a detailed description of the user input of the damage equations please refer to 10 Up to seven entities can be defined the damage equation preferences the single wall ballistic limit equation the multiple wall ballistic limit equation the crater size equation the parametric clear hole equation the advanced hole equation and the user subroutine parameters ESABASE2 Debris Date 2009 09 28 Software User Manual Revision Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 31 55 giele ail 2 2 1 5 User Subroutine For expert users of the original ESABASE the possibility to use your own damage equa tion subroutine is provided This option requires the availability of a FORTRAN o
30. aunschweig taya As an improvement to the Grun meteoroid model the Alpha Beta Separation divides the meteoroids in alpha particles following the Grun sporadic omni directional flux model and smaller beta particles stemming from the sun 2 2 1 1 9 Alpha Beta Separation When you press Edit the Alpha Beta Separation options shown in the screenshot be low appear in a dialog Alpha Beta Options VO cross over velocity 20 0 Gamma exponent 0 16 Figure 2 14 Debris input editor main tab Model Selection Alpha Beta Separation The velocity distribution of the beta particles can be modified by specifying two para meters for more details see 10 e VO cross over velocity default 20 0 km s e Gamma exponent default 0 18 The Alpha Beta Separation obtains improved directional information by attempting to split off the beta meteoroids which are driven away from the Sun into hyperbolic orbits by radiation pressure from the alpha meteoroids An apex enhancement of the alpha meteoroids and interstellar streams see next sub subsection may introduce further directional information We do not recommend using other values than the default values for this model unless you have in depth knowledge in astrophysics ESABASE2 Debris Date 2009 09 28 Software User Manual Revision Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc State Final draft etamax space GmbH Richard Wagner
31. bris flux calculation but does not fully reflect the current knowledge of the Earth s debris environment in particular the existence of a large number of particles on eccentric orbits Upon clicking the Edit deal button the NASA90 input parameters dialog is opened as shown in the screenshot below Debris Model NASAS Options Debris density Far constant density gfcm 3 2 8 Annual mass growth 0 05 Annual Fragment growth 0 02 The solar Flux 10 22 Wm2 Hz 70 0 Minimum debris impact velocity km s Maximum debris impact velocity km s EN Cancel Figure 2 8 Debris input editor main tab Model Selection NASA90 As with all debris models the average density of the debris material can be specified The debris mass P and fragments number Q annual growth rates are specified as per centage where 1 100 growth It is recommended to use the default values Solar flux is used to specify the solar activity appropriate values for the mission dura tion can e g be retrieved using the publicly available SWENET database 22 At the bottom you see the debris velocity range namely the minimum and maximum debris impact velocity to be considered The default is from 0 to 20 km s Please note that the NASA90 model is restricted to orbital altitudes below 1000km ESABASE2 Debris Date 2009 09 28 Software User Manual Revision Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc State Final
32. d and on the Debris page choose User Subroutine as shield type see also section 2 1 Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc Page 32 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig 2 2 2 Debris Ground Test Tab At the bottom of the Debris input editor the second tab leads to the Ground Test page which is depicted in the figure below AF rubesat debris pr Ground Test Shielding Parameters Damage Type Ballistic Limit Iv Thickness 1 0 cm Density m g cm 3 Shielding Type Single Wall EI Failure and Damage Equation Single Wall Ballistic Limit Equation Thick Plate E Input Parameters Visualisation Angle deg Min 0 0 Max 89 0 Mb of steps 10 Fixed value Angle deg iv Fixed To 0 0 m Particle density g cm 3 Min 1 5 Max 1 5 Mb of steps 0 Velocity km s Min 20 0 Max 30 0 Mb of steps 10 Y Axis velocity km s ve Debris Ground Test Non Geometric Analysis Figure 2 20 Debris input editor Ground Test tab The ground test option enables you to run the damage equations on their own outside of the ESABASE2 Debris analysis its purpose is to test and preview the results of the damage equations The following sections are available e Ground Test Choose damage type ballistic limit or crater size and shielding type single wall or multi wall
33. d Wagner StraBe 1 38106 Braunschweig Page 5 55 etauE Si V Glossary Ballistic limit The minimum particle diameter which is able to pene trate a given wall configuration Eclipse Eclipse is an open source community whose projects are focused on providing an extensible development plat form and application frameworks for building software For detailed information refer to http www eclipse org ESABASE Unix based analysis software for various space applica tions For details refer to the ESABASE User Manual 4 ESABASE Debris ESABASE framework and the debris and meteoroid flux and damage analysis application ESABASE2 New ESABASE version running on PC based Windows platforms to be distinguished from the old Unix based ESABASE Geometric al analysis Flux and damage analysis of a full three dimensional geometric model Object pointing keyword tracking of a GEO satellite Ground test Evaluation of the results of a selected damage or failure equation MASTER 2001 ESA s Meteoroid and Space Debris Terrestrial Environ ment Reference Model For details refer to the MASTER Upgrade Final Report 5 ESABASE2 Debris uses the MASTER 2001 Standard application MASTER 2005 ESA s successor to MASTER 2001 now defined as standard application for space debris risk analyses NASA90 Simple analytical space debris engineering model estab lished by NASA 16 NASA96 ORDEM96 NASA s space debris engineering model Succ
34. dditionally they are written in ASCII format to the Listings subfolder of the current project folder in order to be more easily accessible to post processing tools 2 4 4 Notes The figure below shows the Notes tab within the Debris result editor E gt Landsat _debris result 2009 07 06 16 41 06 Here you can enter notes for this result file Motes Listings 3D Results 20 Results Figure 2 40 Debris result editor 2D Results notes It consists of a simple text area where you can write your notes concerning the debris results Your text will be saved and is available to whomever you may send the file ESABASE2 Debris Date 2009 09 28 Software User Manual Revision Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 55 55
35. e 1 38106 Braunschweig giele ail Document Information I Release Note Name Function Date Signature Established by K Ruhl Technical Project 2009 09 28 Manager Released by K D Bunte Project Manager 2009 09 29 Il Revision History 2009 09 28 All Update after review Ill Distribution List diverse n a ESABASE2 licensees ESABASE2 Debris Date 2009 09 28 Software User Manual Revision 1 0 Reference R077 232rep 01 00 Software User Manual Solver Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 3 55 etauE SB IV List of References 1 2 EN 4 5 6 TI 8 El 10 11 12 13 14 15 Date Revision State Page 4 55 K Ruhl K D Bunte ESABASE2 Framework software user manual R077 230rep ESA ESTEC Contract 16852 02 NL JA PC Version of DEBRIS Impact Analysis Tool etamax space 2009 A Gade K D Bunte ESABASE2 Debris Technical Description ESA ESTEC Contract 16852 02 NL JA PC Version of DEBRIS Impact Analysis Tool etamax space July 2009 ESABASE2 homepage http www esabase2 net ESABASE User Manual ESABASE GEN UM 070 Issue 1 Mathematics amp Software Division ESTEC March 1994 Giunta Lemcke C Roussel J F COMOVA 1 1 Technical Description ESTEC Contract No 12867 98 NL PA HTS AG and ONERA March 2002 Giunta l Lemcke C Roussel
36. e 2 6 Figure 2 7 Figure 2 8 Figure 2 9 Figure 2 10 Figure 2 11 Figure 2 12 Figure 2 13 Figure 2 14 Figure 2 15 Figure 2 16 Figure 2 17 Figure 2 18 Figure 2 19 Figure 2 20 Figure 2 21 Figure 2 22 Figure 2 23 Figure 2 24 Figure 2 25 Figure 2 26 Figure 2 27 Figure 2 28 2009 09 28 on 1 0 Final draft Page 8 55 Geometry editor Debris page 12 Debris shielding parameters min wza unakuna nawa 13 Debris input editor main Lab 15 Debris input editor main tab Model Selection 16 Debris input editor main tab Model Selection MASTER 2001 17 Cumulative flux vs particle diameter for an ISS like orbit MASTER 001 ee ee ee ee ee 18 Debris input editor main tab Model Selection MASTER 2005 20 Debris input editor main tab Model Selection NASA9Q 21 Debris input editor main tab model selection ORDEM 2000 22 Debris input editor main tab Model Selection Gr n 23 Debris input editor main tab Model Selection Divine Staubach 24 Debris input editor main tab Model Selection MEM 25 Debris input editor main tab Model Selection Streams 26 Debris input editor main tab Model Selection Alpha Beta Separation 27 Debris input editor main tab Model Selection Apex En
37. e context menu which contains the following options e Colour Defines the result value to be laid over the S C geometry default is total impact flux e Orbital Point Whether to show results for the entire mission single orbital points or an orbital arc e Coordinate Systems Whether to display coordinate systems alongside the S C geometry e Element Chart Shows the results for one single geometrical element select one with Shift Leftclick to enable 2 4 1 1 Colour Debris results come in multiple variables e g impact flux or failure flux and either per year or over the entire mission time Only one of these variables at a time can be laid over the geometry model To choose a result set to be displayed rightclick the 3D view to open the context menu then choose Colour gt lt Variable gt as shown in the following figure E gt Landsat _debris result 2009 07 06 16 41 06 5 D gg G TT T ei n E ky WE mw M 2 year Orbital Point 4 Element Chart Sp Orbital Point k Object Number Coordinate Systems Surface Number Element Number KS Factor Average Impact Velocity km s Average Impact Angle deg Crater Flux Sa year Total Impact Flux 1 m 2z vear Total Impact Fluence 1 m 2 Total Failure Flux 1 m2 year Total Failure Fluence m 2 Notes Listings 3D Results 20 Results Figure 2 32 Debris result editor 3D Results colour context menu etamax space GmbH Richard Wag
38. e population only Explosion Fragments Future population only Figure 2 5 Debris input editor main tab Model Selection MASTER 2001 Apart from the assumed debris density default 2 8 g cm as material mix average the MASTER 2001 model is based on numerical modelling of various population sources which can be included or excluded from an analysis e Launch and mission related objects payloads and satellites upper stages sup port structures These are mostly larger trackable objects o Note that the Westford needles experiment is included as subpopulation and cannot be turned off with this flag e Fragments collision and explosion before reference epoch 2001 05 01 These are known fragment populations e NaK droplet releases coolant droplets released from Russian RORSAT satellites e SRM solid rocket motor firing waste products o slag produced in the final firing phase mostly gt 1 mm o Aluminium oxide AI 0 dust ESABASE2 Debris Date 2009 09 28 Software User Manual Revision 1 0 Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 17 55 Revision 1 0 etan il Paint flakes are generated by surface degradation effects mostly sunlight and thermal cycling e Ejecta are small fragments of the S C created by the impact of debris or meteor oids e Collision but not explosion fragments after refe
39. ed by different companies under ESA contract ESABASE2 adds a modern graphical user interface enabling the user to interactively es tablish and manipulate three dimensional spacecraft models and to display the selected orbit Analysis results can be displayed by means of the colour coded surfaces of the 3D spacecraft model and by means of various diagrams The development of ESABASE2 was undertaken by etamax space GmbH under the European Space Agency contract No 16852 02 NL JA The first goal was to port ESABASE Debris and its framework user interface to the PC platform Microsoft Win dows and to create a modern user interface From the start the software architecture has been expressively designed to accommo date further applications the solvers outlined in the first paragraph were added and more modules like e g Radiation are to follow ESABASE2 is written in Fortran 77 ANSI C and Java 6 The GUI is built on top of the Eclipse rich client platform with 3D visualisation and STEP import realised by Open CASCADE Report and graphs are based on the JFreeReport JFreeChart libraries This user manual is the Debris handbook It complements the Framework user manual 1 which explains the common functionality of all solvers e g Debris Sunlight Atmos phere lonosphere or COMOVA Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc
40. enit Angle 0 0 dea Plate Area 1 0 m 2 Failure and Damage Equation Selection Single Wall Ballistic Limit Equation Thick Plate v Crater Size Eq Thick Plate v Result Log Debris Ground Test Non Geometric Analysis Figure 2 22 Debris input editor Non Geometric Analysis tab In the tab four sections are visible e Non geometrical Analysis Specifies shielding type as well as shield thickness and density and spacing in case of double walls e Orientation and area Specifies the plate size and its orientation or randomly tumbling property e Failure and Damage Equation Selection Specifies the damage and failure equa tions and their options e Result Log Execution log of the analysis run former listing file ESABASE2 Debris Date 2009 09 28 Software User Manual Revision 1 0 Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 35 55 taya 2 2 3 1 Non Geometrical Analysis The following screenshot shows the Non Geometrical Analysis section and the corre sponding Failure and Damage Equation Selection section below it for single and multi wall selection Non geometrical Analysis Non geometrical Analysis Shielding Type EI Shielding Type ae Thickness D 1 cm Density 2 73 gjem 3 Thickness ist plate 0 1 cm Density ist plate 2 73 g om 3 Thickness 2nd plate 1 cm Dens
41. essor of NASA90 and predecessor of ORDEM2000 For details refer to the ORDEM96 documentation 17 non geometric al analysis Flux and damage analysis of a plate which can be speci fied as a randomly tumbling plate or an oriented plate ORDEM2000 NASA s latest space debris engineering model For details refer to the ORDEM2000 documentation 15 STEP Acronym which stands for the Standard for the Exchange of Product model data Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc Page 6 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig VI List of Abbreviations Abbreviation GUI Graphical User Interface JVM Java Virtual Machine MASTER Meteoroid and Space debris Terrestrial Environment Reference Model MLI Multi layer insulation NASA National Astronautics and Space Administration OCAF Open CASCADE Application Framework contains the ESABASE2 data model ORDEM Orbital Debris Engineering Model RTP Randomly Tumbling Plate ESABASE2 Debris Date 2009 09 28 Software User Manual Revision Reference R077 232rep 01 00 Software User Manual Solver Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 7 55 giele ail VII List of Figures Date Revisi State Figure 2 1 Figure 2 2 Figure 2 3 Figure 2 4 Figure 2 5 Figur
42. ge flux distributions e Listings In tradition of the original ESABASE this tab shows the LIS files pro duced by the Debris solver e Notes A blank text area for your own notes 2 4 1 3D Results The following figure shows the 3D Results tab in a debris result editor 9 FSABASE2 File Edit Window Help CS H L GTI Reset perspective Gr har E ESABASE2 Explorer E Landsat _debris result 2009 07 06 16 41 06 7 9 2 om 1 eg A mo tc 07 landsat diio g 9 oad D e eM En Landsat ES Landsat _debris result 2009 07 W Landsat7 debris Landsat7 mission Total Impact Flux 1 m 2 year Orbital Point 4 lt De Outline T Box H STATE C INFO C DEBRIS T Box BO lt gt E Properties Property ID Notes Listings 3D Results 2D Results Figure 2 31 Debris result editor 3D Results You can see a spacecraft geometry Landsat7 with total impact flux visualised by col our codes on the elements and decoded by the colour scale on the right At the top of the editor the same toolbar as in the geometry editor appears allowing you to zoom rotate and scroll around the spacecraft x 0039 09 28 ESABASE2 Debris sion 1 0 Software User Manual Final draft Reference R077 232rep 01 00 Software User Manual Solver Debris doc e 44 EL etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig giele ail Additionally you can rightclick into the 3D area to invoke th
43. hancement 28 Debris input editor main tab Size Boundaries eese 29 Debris input editor main tab Ray Tracing cccccscecseeeesseeeeseeeeseeeesaees 30 Debris input editor main tab Damage Model 31 Finding the User subroutine DL 32 Debris input editor Ground Test Lab 33 Debris input editor Ground Test tab Run 34 Debris input editor Non Geometric Analysis tab 35 Debris input editor Non Geometric Analysis tab Single and Multi wall 36 Debris input editor Non Geometric Analysis tab Orientation and Eeer 36 Geometric Debris analysis Run button 38 Geometric Debris analysis Run vwizard sees 39 Geometric Debris analysis Run dialog export page 40 Geometric Debris analysis Progress bar 41 ESABASE2 Debris Software User Manual Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Figure 2 29 Figure 2 30 Figure 2 31 Figure 2 32 Figure 2 33 Figure 2 34 Figure 2 35 Figure 2 36 Figure 2 37 Figure 2 38 Figure 2 39 Figure 2 40 Non geometric Debris analysis Run wizard Non geometric Debris analysis results 43 Debris result editor 3D Results esses nennen 44 Debris result editor 3D Results colour context menu
44. ion When you click on the Edit button a dialog with MASTER 2005 input parameters will open as show in the following figure Debris Model MASTER 2005 Options Debris density For constant density gfem 3 2 6 Launch and mission rel objects Mak droplets SRM slag particles SRM Al203 dust historic population only Paint Flakes historic population only Ejecta historic population only Collision Fragments s s s s s s S s Explosion Fragments Figure 2 7 Debris input editor main tab Model Selection MASTER 2005 The MASTER 2005 options are similar to the MASTER 2001 options see previous subsub section The following differences have to be noted e Collision and explosion fragments cover both historic and future populations not only future populations as in MASTER 2001 o This also explains why the Fragments historic option has vanished in comparison to MASTER 2001 Like MASTER 2001 MASTER 2005 covers altitudes from 150 km to 37000 km The fu ture is from 2005 05 01 and in the future objects lt 1 mm are not considered Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc Page 20 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig 2 2 1 1 3 Debris model NASA90 NASA90 16 is an analytical debris model developed by NASA which provides a simple and very fast de
45. ity 2nd plate 2 73 gfcm 3 Space between 10 0 cm Failure and Damage Equation Selection Failure and Damage Equation Selection Single Wall Ballistic Limit Equation Thick Plate Iv Multi Wall Ballistic Limit Equation ESA Triple iv Figure 2 23 Debris input editor Non Geometric Analysis tab Single and Multi wall The input values correspond to the ones used in the geometry editor in the Debris page of the shape wizards see 2 1 2 2 3 2 Plate Orientation and Area The figure below shows the Plate Orientation and Area section within the Non Geometric Analysis tab Orientation and Area Orientation and Area Randomly Tumbling Randomly Tumbling Azimuth Angle 0 0 deg zenit Angle 0 0 deg Plate Area 1 0 m Plate Area 1 0 m 2 Figure 2 24 Debris input editor Non Geometric Analysis tab Orientation and Area Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc Page 36 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig giele ail e Randomly tumbling This is the random tumbling plate RTP mode It often cor responds to the environment models themselves and is an effective way to get a quick first order assessment of the micro particle environment risk for a mission The plate orientation can be one of the following e Oriented For this mode azimuth and zenith angles of the
46. ner StraBe 1 38106 Braunschweig Page 45 55 giele ail The first 4 items listed below are not part of the Debris results instead they are used to gain an overview of the spacecraft geometry and particular its objects surfaces and elements e Colour Displays exactly the same object colour which was used in the geometry editor e Object Number Each object is identified by an object number In this overlay this object number is mapped to colours o Leftclick on an object in the 3D view to select it and then look at the col our scale to the right The appropriate colour will be marked and the ob ject number will be shown e Surface Number Breaking down the objects each surface is shown in a different colour o Ctrl leftclick on a surface in the 3D view to select it The respective surface number is marked in the colour scale to the right e Element Number Further breaking down the surfaces each element is shown in a different colour o Shift leftclick on an element in the 3D view The selected element num ber and color will be marked in the color scale The following 8 items show the respective quantity listed below as colours on the ele ments of the geometry model To see the exact value on an element Shift leftclick the element the colour scale on the right will then show the quantity value e KS Factor e Average Impact Velocity km s e Average Impact Angle deg e Crater Flux year e Total Impact Fl
47. ometric Debris Analysis Geometric Debris Analysis Please choose the input Files Far the analysis Project debris testing Satellite test uc 5 OU Full Mission test uribc 5 DASS Debris test ufike 5 06IMZ2005 D05 Only preprocessing to verify pointing and kinematic Faster slim Results no 3D results will be created Generate output Filename Filename debris result 2009 07 06 22 27 57 Report options Complete listing of all w Figure 2 26 Geometric Debris analysis Run wizard In the first line you specify a project from your workspace then the next three combo boxes will only show files from this project A spacecraft geometry a mission file and a debris input file must be chosen Activating the Only Preprocessing checkbox will stop the analysis after pointing and kinematics have been calculated It is useful to check the correctness of the pointing and kinematics settings without running a complete and possibly time consuming de bris or meteoroid analysis The Slim Results checkbox is a performance switch With it LIS files as in the origi nal ESABASE and 2D graphs will be created as usual and with full information content as specified in the Report Options box but the only 3D geometry result will be for the entire mission no orbital points or arcs will be available For large models or many orbital points this may be the only option to run ESABASE2 Debris within the available RAM of the exec
48. ough double wall parameters 21 or user subroutine only for expert users with Fortran and or C experience see 2 2 1 5 Depending on single multiwall choice some fields are enabled or disabled In the screenshot above you see Singlewall chosen and thus material density and thickness of only one shield plate enabled If you select Multiwall instead you need to specify material density and thickness for the second shield plate or back up wall as well as the spacing between both plates Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc Page 12 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig giele ail The figure below illustrates the parameters from the Wizard whole or scattering whole or scattering particle Backup wall Komm OO __ thickness spacing thickness plate 1 plate 2 Figure 2 2 Debris shielding parameters A particle hits the first shield wall and the effect depends besides the impact velocity the impact angle and particle properties such as its diameter and material density on the material density and thickness of the wall The particle is either stopped or pene trates the wall it can remain whole or be scattered into smaller pieces due to the im pact If it penetrates it travels the spacing between the walls the same stop penetration scatter happen
49. r C C compiler and linker You need to rebuild the gt UserSubroutine dll Dynamic Linked Library located in the release dlls directory of the installation as shown in the figure below Ordner Name SG ESABASE2 2 0 0 2009 07 02 SS DFORMD DLL components E E E2 DatalibFacade dll configuration E Ez EsabaseAtomax dll O logs E E EsabaseDebris dll H plugins S E2_UserSubroutine dl D BRAGE E gdiplus dil HO Solver S logscxx dil H LH workspace i5 mFce0 dl Figure 2 19 Finding the User subroutine DLL ESABASE2 2 0 0 uses the Compaq Visual Fortran 6 compiler It is highly advisable to use the same compiler Also while it is possible to use other languages e g C to pro duce the subroutine DLL compiler issues frequently occur Please note When writing your own user subroutine in Fortran take care to initialise all variables otherwise results can be erratic As a starting point look at the Fortran file user dam f in the Debris plugin directory plugins NVeu esa estec esabase2005 debris 2 0 0 user subroutine In case of persisting issues please contact the ESABASE2 development team using the email address pro vided on the website 3 To apply the subroutine to the entire model choose User Subroutine as damage equ ation in the Debris input editor as described above subsection 2 2 1 4 To apply it only to parts of the S C geometry go to the geometry editor modify a shape via wizar
50. rence epoch covers assumed collision rate of satellites with other bodies in the future e Explosion but not collision after reference epoch covers assumed explosion rate of satellites in the future In the context of the MASTER 2001 model reference epoch or historic means dates until 2001 05 01 The future are dates from 2001 05 01 note that from there objects 1 mm are not considered this also means that paint flakes ejecta and dust are not available because they are always 1 mm As an example of the effect of the various factors the figure below shows the cumula tive cross sectional debris flux from different sources on an ISS like orbit 1e 006 launch mission rel obj 10000 fragments Mak droplets B 100 SRM slag SRM AI2O3 dust E i paint flakes EN ejecta T 0 01 T 5 sum of all c 0 0001 18 006 1e 008 1e 010 1e 012 ELLO 1e 006 1e 005 0 0001 0 001 0 01 0 1 1 10 100 impactor diameter m Figure 2 6 Cumulative flux vs particle diameter for an ISS like orbit MASTER 2001 MASTER 2001 provides realistic yearly population snapshots for the past and the future The flux calculation is based on the analytic evaluation of the distributions of the size and the orbital elements of the particle population MASTER 2001 Standard applica tion The model considers the population asymmetry induced by the asymmetric distribution of the particle orbits argument of perigee
51. rface ma terial properties as defined by the Material page are not interpreted by the Debris solv er Please note that the Debris page is only available if ESABASE2 Debris is part of your in stallation it is also possible to have only ESABASE2 Atmosphere for example depend ing on your license ESABASE2 Debris Date 2009 09 28 Software User Manual Revision Reference R077 232rep 01 00 Software User Manual Solver Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 11 55 taya To see the Debris page open a geometry file select a shape then rightclick it and choose Modify gt Debris A wizard page as shown in the figure below will be opened 2 Shape Wizard Debris Size Meshing Position amp Attitude Kinematic Pointing Debris Material Shield type only for geometrical analysis Singlewall iv Material density 2 713 a cm 3 Material density 2nd plate a cm 3 Spacing cm Thickness plate 1 0 1 cm Thickness plate 2 cm Cancel Figure 2 1 Geometry editor Debris page On this page you can define shielding and material parameters that go beyond the Ma terial page of the shape wizard The simplest option is to check the Inherit parent values checkbox which takes over all Debris related values from the parent shape This is possible for all shapes except the central body Below the shield type can be chosen Singlewall multiwall specified thr
52. ry rays parameter specifies the number of secondary rays to be fired from each impact point Due to the high computational effort caused by this option it is recommended to choose fairly low values lt 100 Another option to reduce computation time is to specify a Secondary ray jump which causes the program to skip the respective number of secondary rays Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc Page 30 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig 2 2 1 4 Damage Model There are two types of damage equations used during the analysis e The ballistic limit equations which deliver the limit impactor diameter above which a structural failure of the analysed surface occurs This limit diameter is used to compute the probability of a failure using the chosen flux models e The damage size equations which compute the crater diameter of semi infinite targets and the hole size of thin targets Again the flux models are then used to compute the total cratered or perforated area of the surface The figure below shows the damage parameters in the main tab Damage Model Failure Equation Damage Equation single wall Thick Plate Crater Size Thick Plate EN CO Multi Wall ESA Triple m Edit Clear Hole Maiden E Use Geometry Advanded Hole Aluminium m Use User Subroutine
53. s with the second wall Depending on the remaining energy the particle causes a a crater on or b a penetration of the device behind the wall In a single wall scenario the second wall does not exist and the likelihood of a crater or penetration is considerably increased A failure equation determines whether a particle penetrates the wall configuration A damage equation determines the size of the crater or hole depending on no penetra tion penetration on the first wall shield More information can be found in the ESABASE2 Debris technical description 2 and in the IADC Protection Manual 21 This concludes the Debris specific additions to the geometry file ESABASE2 Debris Date 2009 09 28 Software User Manual Revision 1 0 Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 13 55 giele ail 2 2 Debris Input Complementing the Debris parameters bound to the geometry see previous section the global Debris Meteoroid input parameters are all specified in the Debris input edi tor This editor is divided into three tabs e Debris Main Tab Specifies the parameters for the geometrical analysis e Ground Test Tab An efficient way to test damage equations e Non Geometric Analysis Tab Allows a fast guess for the expected flux values on a specific orbit 2 2 1 Debris Main Tab The main tab of the Debris input
54. traBe 1 38106 Braunschweig 2 2 1 1 5 Meteoroid model Gr n Gruen 14 is an interplanetary flux model for sporadic meteoroid environment When you press the Edit button a dialog with the Gruen input parameters shown in the figure below apppears Fleteoroid Model Gruen Options Meteoroid density For constant density g om 3 S Meteoroid density model Constant Iv Meteoroid velocity model Constant v Constant meteoroid impact velocity cansk velocity only km s 17 0 Minimum meteoroid impact velocity Nasa90 and HAMP only km s 11 0 Maximum meteoroid impact velocity Nasa90 and HRMP only kms 72 0 Figure 2 10 Debris input editor main tab Model Selection Gr n On top you see the meteoroid density option Below choose between this constant meteoroid density and alternatively the NASA90 density distribution model the latter choice will ignore your meteoroid density specification above The next two lines are concerned with the meteoroid velocity distribution option e Constant meteoroid velocity for this option the default value is 17 km s e The NASA90 velocity distribution In most cases this delivers the best results and is thus the recommended option for the industrial user e The Taylor HRMP velocity distribution This model is the most complex option The last two lines handle the meteoroid velocity range namely the minimum and maximum meteoroid velocity to be considered The default is
55. uth F f elevation for each orbital point F f m F f azimuth F f elevation F f velocity for each orbital point Table 2 1 Available 2D charts in dependency of the Debris Meteoroid model Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference R077 232rep 01 00 Software User Manual Solver Debris doc Page 50 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig giele ail The 2D Result tab offers additional functionality to work with the charts represented by buttons to the right of the chart combo box e Options Allows you to customise the chart appearance e mage Export Save the current chart to a PNG or JPG file e Show Report Opens a print ready report for a given chart 2 4 2 1 2D Charts Options The Options button opens a context menu for a given chart as shown in the follow ing figure It contains axis configurations as well as settings for the data lines ES Landsat debris result 2009 07 06 16 41 06 2 mL Graph MOS vel op01 v Label text k Grid Title k Label Font MASTE vr gt Leit os Clty orbital point 01 Background Label Font style H w Box Maximum Foreground Minimum E 6 w Auto scaling Number Format 5 Graph Type Number scaling E Series 0 k 4 Export m Range x 3 u 1 JL LN 00 25 50 75 100 125 150 175 200 225 250 275 300 325 350 375 400 Velocity km s
56. uting computer Generating an output filename is highly recommended The default filename contains the solver type here debris and the current date and time ESABASE2 Debris Date 2009 09 28 Software User Manual Revision Reference R077 232rep 01 00 Software User Manual Solver Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 39 55 giele ail At the bottom the Report options combo box allows you to specify the content of the Deb Met listing formerly LISD LISM LISDM output files within the Debris result file You can choose between the following options e Output of a summary of objects results on orbital arc and mission level and on object and spacecraft level no object element summary no orbital point related results and no element related results e Output of header and summary all the same but including object element summary and element related results e Complete listing of objects orbital point orbital arc and mission related results on object and spacecraft level no object element summary and no element re lated results e Complete listing of all the same but including object element summary and element related results Optionally you can press the Next button to go to the second page of the Debris analysis wizard which is depicted in the figure below 9 Geometric Debris Analysis Export to ZIP file Please select if you want to
57. ux 1 m 2 year e Total Impact Fluence 1 m 2 e Total Failure Flux 1 m 2 year e Total Failure Fluence 1 m 2 If the secondary ejecta option was activated in the Debris input editor it is now addi tionally possible to display the direct impact failure flux fluence and the ejecta im pact failure flux fluence Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc Page 46 55 etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig 2 4 1 2 Orbital Point When the debris result editor opens it shows the analysis results for the entire mission You can also view the results for each orbital point or for the orbital arc Open the con text menu and navigate to Orbital Point as shown in the following figure Es Landsat _debris result 2009 07 06 16 41 06 5 v DI e m3 en Ta L d IK oa KA WA e H mi ei ty E 1 Orbital Point 4 Colour V Coordinate Systems Orbital Arc Orbital Point 1 Orbital Point 2 Orbital Point 3 Orbital Point 4 Notes Listings 3D Results 2D Results Figure 2 33 Debris result editor 3D Results Orbital Point context menu Choose one of the following e Mission The entire mission duration e Orbital Arc One orbital arc only e One of the orbital points Results at a dedicated orbital point When you select an orbital point then Earth Sun and velocity direction are shown as
58. x the Jen niskens stream model adds annual meteoroid streams e g the Perseids The streams model can be used with or without another meteoroid model When pressing the Edit button the dialog for the Jenniskens Stream Model input parameters appears as shown in the figure below Streams Options File for Streams Istreamsljen str Lower CUE OFF mass 0 0 Figure 2 13 Debris input editor main tab Model Selection Streams The streams and possible interstellar sources are defined in an external input file with a default jen str being provided by ESABASE2 File locations are always relative to the ESABASE2 installation path Meteoroid particles with less mass than the lower cut off mass are not considered in the analysis The Jenniskens stream model is based on observation data gathered over a 10 year pe riod and can be applied to flux and damage analysis It also includes directional infor mation on the streams Please note that for long mission durations the directional effect is smeared out and does not give any additional information than the Gr n sporadic option The stream option is best suited for the investigation of missions below 10 days where high stream activities are expected Date 2009 09 28 ESABASE2 Debris Revision 1 0 Software User Manual State Final draft Reference RO77 232rep_01_00_Software_User_Manual_Solver_Debris doc Page 26 55 etamax space GmbH Richard Wagner StraBe 1 38106 Br
59. x vs velocity orbital point 01 Figure 2 38 Debris result editor 2D Results reporting This report details the chart properties and below the chart itself followed by the data values represented in the chart on the second and following pages It is thus a com plete data description of a value pair s relation suitable for distribution to your col leagues You may either print the report press the print button or choose Export gt Save as PDF for electronic distribution ESABASE2 Debris Date 2009 09 28 Software User Manual Revision Reference R077 232rep 01 00 Software User Manual Solver Debris doc State Final draft etamax space GmbH Richard Wagner StraBe 1 38106 Braunschweig Page 53 55 taya 2 4 3 Listings The original ESABASE produced LIS files or listing files containing all debris results in one text file This ability is also available in ESABASE2 in order to stay compatible to many post processing tools The listings are shown on the Listings tab of the debris result editor as shown in the figure below Ex Landsat debris result 2009 07 06 16 41 06 0 m Result Log Deb Met Dout E ORBITAL POINT NUMBER 1 ol CLASSICAL ORBITAL ELEMENTS A 6775 20 km E 0 0000045 Inclination 51 600 deg RAAN 0 000 deg ArgotPer 0 00 deg True Anomaly 0 000 deg True Latitude 0 EL Ks Fc Imp ngle Imp Vel Crat Area Imp Flux Imp Flue Mb Impacts Fail Flux F degrees km s amp wr

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