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UNIVERSITY OF LIEGE Department ArGEnCO Service Structural

1. DIAMOND Figure 1 files and steps 23 02 2011 12 2 3 General Data for Structural Analysis The general data for the IN file of a structural analysis is briefly presented in Table 2 In each input line a command is given followed by the parameters for the command Full details of all the commands are given in Chapter 3 Table 2 Input data file IN format for structural analysis Command Parameter Format Notes lt A80 gt Comments multiple lines possible Blank line for end of comments NNODE NDIM NDOFMAX EVERY NODE Optional ia FROM N1 TO N2 STEP N3 NDOF N4 Optional multiple lines possible REAPEAT REPEAT N1 TO N2 STEP N3 TIMES N4 END_NDOF end of the section STATIC The user has to indicate following the word OR STATIC or DYNAMIC the resolution technic DYNAMIC choosen Either PURE NR or APPR_NR NLOAD OBLIQUE COMEBACK OR Only COMEBACK needs a parameter NOCOMEBACK NORENUM OR RENUMPERM OR RENUMGEO OR f RENUM Only RENUMGEO needs a parameter either 0 or OR a node number READRENUM NMAT ELEMENTS BEAM Optional NG For beam elements NFIBER For beam elements TRUSS Optional SHELL Optional NGTHICK For shell elements NGREBARS For shell elements
2. T KE Kfy Kfp EPSth 0 L i 200 1 0 95 0 90 1 S00 0 1 0 15 Q1 1200 O O BIAXIAL PLANE STRESS MATERIAL TYPES If CMAT ELPLANESTR PARACOLD 1 NM Young s modulus PARACOLD 2 NM Poisson ratio PARACOLD 3 NM Coefficient of thermal expansion Elastic plane stress material law The material is valid for steel at elevated temperature and the Young s modulus and thermal strain vary according to the Eurocode 3 part 1 2 If CMAT PLSTRVML PARACOLD 1 NM Young s modulus PARACOLD 2 NM Poisson ratio PARACOLD 3 NM Yield strength PARACOLD 3 NM Strain hardening modulus This model is a simplified model for steel at elevated temperature with a bilinear equivalent stress strain relationship The model STEELEC32D is to be preferred if no problem of convergence is encountered The parameters vary according to the Eurocode 3 part 1 2 variation of the strain hardening modulus as for the Young s modulus If CMAT STEELEC32D PARACOLD 1 NM Young s modulus PARACOLD 2 NM Poisson ratio PARACOLD 3 NM Yield strength PARACOLD 4 NM Maximum temperature for a reversible behaviour during cooling PARACOLD 5 NM Rate of decrease of the residual yield strength when the maximum temperature has been greater than PARACOLD 4 NM N m kK 23 02 2011 40 If CMAT CALCONC2D S ILCONC2D PARACOLD 2 NM PARACOLD 3 NM PARACOLD 4 NM PARACOLD 5 NM Poisson ratio Compressive strengt
3. 0 if peak stress strain recommended value gt 0 if peak stress strain maximum value more ductile If CMAT CALCONC_EN SILCONC_EN LWCONCEC2 PARACOLD 2 NM Poisson ratio PARACOLD 3 NM Compressive strength PARACOLD 4 NM Tensile strength If CMAT CALCONC_PR SILCONC_PR PARACOLD 2 NM Poisson ratio PARACOLD 3 NM Compressive strength PARACOLD 4 NM Tensile strength PARACOLD 5 NM Time at which this concrete is cast Before and until this time the material does not carry any stress or have any stiffness If CMAT CALCO_COLD SILCO_COLD PARACOLD 2 NM Poisson ratio PARACOLD 3 NM Compressive strength fom in N m Note the following equations are embedded in SAFIR 23 02 2011 37 f 0 0 E 105x2000 La for SILCO COLD E 1 05x0 9x22000 4 for CALCO_COLD SHPO fe x10 lt 2 8x10 3 5x10 if f lt 50 cu cm 4 A 2 8 27 Bada xl0 if f n gt 50 100 with fon in MPa M II M II If CMAT PARABCONC PARACOLD 1 NM E Young s modulus PARACOLD 2 NM Poisson ratio PARACOLD 3 NM Compressive strength PARACOLD 4 NM Tensile strength PARACOLD 5 NM Strain at compressive strength PARACOLD 6 NM Ultimate strain If CMAT AL6061T6C AL5083SUP AL5083INF AL7020SUP AL7020INF aluminium PARACOLD 2 NM fo 2 PARACOLD 3 NM fo PARACOLD 4 NM Erupture IN Yo If CMAT SLS1 4301 SLS1 4401 SLS1 4404 SLS1 4571 SLS1 4003 SLS1 44
4. One line added for each concentrated mass linked to a node M_NODE NNO MASS 1 MASS 2 MASS NDOF NNO Number of the node where the mass are applied MASS 1 Mass linked to degree of freedom 1 MASS 2 Mass linked to degree of freedom 2 MASS NDOF Mass linked to degree of freedom NDOF Notes 1 A mass linked to a displacement is in kg A mass linked to a rotation is in kgm 2 Usually a concentrated mass linked to a displacement is active in all directions Only in soma particular cases can a mass be inactive in a particular direction for example a ball laying on a horizontal surface might be active in the direction perpendicular to this surface and not active in the directions parallel to this surface Mass on beam elements Self Weight One line added for each beam element with a distributed mass applied M_BEAM NBM TRAV 1 TRAV 2 NBM Number of the specific BEAM under a distributed mass TRAV 1 Uniformly distributed mass applied on the beam element kg m 23 02 2011 34 or TRAV 2 Rotational inertia of the beam element section gt Pi Lyi 2 2 With L Slat lat Yea Ait Zooi Ai p Volumic mass of the material i TRAV 2 only present if a 3D analysis is made GM_BEAM NBM TRAV 1 TRAV 2 KGENE NBM Number of the specific BEAM under a distributed mass TRAV 1 Uniformly distributed mass applied on the beam element kg m TRAV 2 Rotational inertia of the beam element se
5. REBARS NBARS of re bar layers in this section type NBARS groups of cards 1 card MATERIAL MAT local of the material of this layer 1 card SECTION A cross sectional area of this layer in m m 1 card LEVEL zZ position of this layer with respect to the thickness 1 card ANGLE angle Angle in degrees between the local x axis and the layer of rebars see Figure below 23 02 2011 54 SERIES 5 e Nodes 1 line Either Points of integration Cold or Hot section lt Al10 gt COLD This section is not heated The temperature in the shell remains or at 20 C gt The TSH file can be ended here No need to write the next groups 7 HOT This section is heated by a time temperature curve the same or TuserShe or curve for all the elements of this type The next groups are necessary 11 This section is heated according to the function that has been programmed by the user in the DLL called SAFIRDLL DLL No need to write the next groups 7 HASEMI This section is heated by a Hasemi fire The next groups are necessary SERIES 6 position of the nodes 1 line lt A24 gt POSITIONS OF THE NODES line lt A25 gt Ww W line lt A21 14 gt NUMBER OF POSITIONS Number_of_position gives the number of nodes which give the tem
6. SOLID Optional NG For solid elements ENDELEM3 end of ELEMENT section NODES or NODES CYL Choose Cartesian or Cylindrical coordinates NODE a AGNODET Multiple lines possible REPEAT Last I5 not present if NODE command is used FIXATIONS 23 02 2011 13 BLOCK Optional multiple lines possible SAME SAMEALL OR Optional multiple lines possible REPEAT END FIX line for end of section NODOFBEAM For beam elements Filename TEM A20 Left justified file name of TEM file for beams TRANSLATE Multiple lines possible for beams END _ TRAN end of section ELEM or GELEM Entry to list nodes of all elements and material type NODOFSOLID Optional Filename TSL File name for TSL file related to solid elements ELEM or GELEM OR Multiple lines possible for solid elements REPEAT ENDSYM For solid elements NODOFSHELL Optional Filename TSH lt A20 gt File name for TSH file related to shell elements TRANSLATE lt I5 gt lt I5 gt As many line as necessary for shell elements ENDTRANSLA End of translation for shell elements ELEM OR lt 9 I5 gt Multiple lines possible for shell elements REPEAT NODOFTRUSS Optional Filename TRS lt A20 gt lt 3 G10 0 gt lt I5 gt File name for TRS file related to
7. local HASEMI fire s for a thermal analysis See Users manual of Safir Thermal docx Section D 1 3 3 3 Description and Format of the IN file for Structural Analysis SERIES 1 SERIES 2 SERIES 3 SERIES 4 SERIES 6 Comments One line for each comment can be 0 line One blank line to mark end of comments Number of nodes One line NNODE NNODE NNODE Number of nodes of the structure Number of axes One line NDIM NDIM NDIM Number of global axes 2 for plane structures 3 for 3 D structures Degrees of freedom One line first line in series 23 02 2011 18 NDOFMAX NDOFMAX NDOFMAX Maximum number of degrees of freedom per node if NDIM 2 for truss elements NDOFMAX 2 2 for solid elements NDOFMAX 2 2 for beam elements NDOFMAX 2 3 if NDIM 3 for truss elements NDOFMAX 2 3 for solid elements NDOFMAX 2 3 for shell elements NDOFMAX 2 6 for beam elements NDOFMAX 2 7 Degrees of freedom for all the nodes EVERY_NODE NDOF NDOF Number of degrees of freedom Note e This line allocates NDOF D o F to all the nodes e lf all the nodes of the structure have the same number of D o F then the END NDOF line mentioned below finishes the series If not additional lines have to be used to mention the nodes which have a different number of D o F The following lines do this e If the line with the command EVERY NODE is not present then all the nodes have 0 D o F an
8. 0 EPSRSOLID Residual stress in this element KGENE Number of times that this command has to be repeated The element numbers increase by 1 For triangular elements NODE 4 NE 0 Note 23 02 2011 49 The following group of lines on symmetry is necessary if symmetry is accounted for If not only the ENDSYM line is present Solid elements symmetry One line lt A10 gt SYMMETRY Solid element axis of symmetry One line for each axis a maximum of six axes can be specified lt A10 gt lt 215 gt REALSYWM N1 N2 N1 First node on axis N2 Second node on axis Note This line means that the line passing by the nodes N1 and N2 is an axis of symmetry When creating the TOR file the fibres located on the other side of the line are created This option is used when there is a thermal axis of symmetry which will not be a structural axis of symmetry in the structural calculation Solid elements axis of symmetry symmetric about y axis One optional line lt A10 gt YSYM Note This line is used for plane beam elements which have this symmetry When creating the TOR file the area of the fibres is simply multiplied by 2 Solid elements last line One line to mark end of series and symmetry lt A10 gt ENDSYM SERIES 11 Precision One line lt A10 gt lt G10 0 gt PRECISION PRECISION PRECISION Sma
9. 25 GELE 32 ELE 33 GELE 40 1 2 3 108 1 15 16 Ie 10S 1 2 18 19 20 108 21 32 33 34 108 1 2 35 36 37 108 1 49 50 51 108 1 2 52 53 54 108 1 66 67 68 108 1 2 69 70 71 108 21 83 84 85 108 1 2 can be replaced by the following one ELEM 1 GELEM 8 REPEAT 8 to generate ELEM NODE 1 NODE 3 NODE 2 NODE 4 TYPE 1 1 2 3 108 0 E4 2 3 4 5 108 0 E4 3 5 6 7 108 O E4 4 7 8 9 08 0 E4 5 9 10 IL 08 0 E4 6 I1 12 13 08 0 E 7 13 14 15 08 0 I 8 LS 16 17 08 0 E4 9 18 19 20 08 0 E4 10 20 21 22 08 0 E4 TL 22 23 24 08 0 E4 12 24 25 26 08 0 E4 13 26 27 28 08 0 E4 14 28 29 30 08 0 15 30 31 32 08 0 16 32 33 34 08 0 17 35 36 37 08 0 18 37 38 39 08 0 19 39 40 41 08 0 20 41 42 43 08 Or 21 43 44 45 08 0 22 45 46 47 08 0 23 47 48 49 08 0 24 49 50 51 08 0 25 52 53 54 08 0 26 54 55 56 08 0 27 56 57 58 08 0 28 58 59 60 08 0 29 60 61 62 08 0 30 62 63 64 08 0 31 64 65 66 08 0 32 66 67 68 08 0 33 69 70 71 08 0 34 71 72 73 08 0 35 73 74 75 08 0 36 75 76 77 08 0 I 1 37 77 78 719 08 0 1200E 01 38 719 80 81 08 0 1200E 01 1 2 3 108 1 15 16 17 108 1 2 17 0 0 4 23 02 2011 29 39 81 82 83 108 1 0 1200E 40 83 84 85 108 1 0 1200E O1 O1 SERIES 17 SOLID elements Not possible at the time being because no 3D material model has been implented and validated SERIES 1
10. N1 Node 1 N2 Node 2 N3 Node 3 23 02 2011 30 N4 Node 4 ITYPESHELL NSH Type of geometrical section KGENE Automatic generation on the element number or lt A10 gt lt I5 gt lt I5 gt lt 30b gt lt I5 gt REPEAT NSH N1 NUMBER NSH Number of elements to be repeated N1 Node increment NUMBER Number of times that the NSH elements have to be repeated 23 02 2011 31 SERIES 19 TRUSS elements Note This series is skipped if no TRUSS element is present in the structure One line first line of possible multiple line series NODOFTRUSS Truss elements files One line for each different truss section type used CFILENAME GEOTRUSS 1 NGT GEOTRUSS 2 NGT IMATTRUSS NGT CFILENAME Name of the file where the temperatures concerning this section types are read Left justified GEOTRUSS 1 NGT Cross sectional area of this section type GEOTRUSS 2 NGT Residual stress of this section type IMATTRUSS NGT Global Number of the material in this section type Note If cfilename NGT is left blank then e this must be the case for all the section types e there is only one element in each NGT e the elements must be linked to nodes which belong to solid elements e the temperature of each truss element is the average of the temperature of its 2 nodes calculated with solid elements Truss elements list One line for each trus
11. and the program capability are presented in this Chapter Details of the data files material properties and cross sectional shapes are presented in Chapter 2 The detail input and format used in the program are given in Chapter 3 while Chapter 4 presents the theory and formulations of the elements available in the program 1 2 Analysis Procedure Using the program the analysis of a structure exposed to fire may consist of several steps The first step involves predicting the temperature distribution inside the structural members referred to as thermal analysis The torsional analysis may be necessary for 3 D BEAM elements a section subject to warping and where the warping function table and torsional stiffness of the cross section are not available The last part of the analysis termed the structural analysis is carried out for the main purpose of determining the response of the structure due to static and thermal loading The various stages of analysis are briefly outlined in the following sections 1 2 1 Thermal analysis This analysis is usually performed while the structure is exposed to fire For a complex structure the sub structuring technique is used where the total structure is divided into several substructures and a temperature calculation is performed successively for each of the substructures This kind of situation does arise in a structure where the members are made of different section types or made of sections sub
12. stress in this fibre 1 group of lines if this group is absent then the warping function is equal to 0 on the cross section 1 line lt A10 gt W w NFIBERBEAM NGB lines lt F12 6 gt WARPING NFB NGB value of the warping function in this fibre 1 line lt A8 E12 6 gt GJ GJ NGB torsional stiffness of the cross section End of the group 23 02 2011 52 1 line lt A10 gt Either COLD This section is not heated The temperature in all fibres remains at 20 C gt The TEM file can be ended here No need to write the next groups TIME NFIBERBEAM or HOT This section is heated The next groups are necessary 1 group of lines Repeat this group of lines for each time step 1 blank line lt A80 gt 1 line lt 7x F8 1 gt y TIME 1 blank line lt A80 gt NFIBERBEAM NGB lines lt 5x F6 1 gt TEMPBEAM 2 NFB NBG temperature in the fibre NGB 23 02 2011 53 3 6 Structure of the TSH files used with the shell F E SERIES 1 Comments Any number of lines comment cards lt A80 gt 1 blank line indicating that the comments are finished SERIES 2 Thickness of the shells 1 line THICKNESS THICKSHELL Thickness of this section type SERIES 3 Material of the shells 1 line MATERIAL MAT Local material number of this section type This is the material of the plain section to which layers of re bars can be added SERIES 4 Layers of re bars 1 line
13. where stresses are printed PRINTET NBM NG Print the tangent moduli in a beam element NBM Number of beam element where moduli are printed NG Integration point of the beam element where moduli are printed PRNEPSMBM NBM NG Print the mechanical strains in a beam element En NBM Number of beam element where mechanical strains are printed NG Integration point of the beam element where mechanical strains are printed PRNSIGMASH NSH Print the stresses in a shell element NSH Number of the solid element where the stresses are printed PRINTSHELL Equivalent to PRNSIGMASH for all the shell elements large amount of results PRNNXSHELL Print the membrane forces Nx Ny and Nxy N4 N2 and a in the shell elements PRNMXSHELL Print the bending moments Mx My and Mxy M M and a in the shell elements PRNEASHELL Print the membrane stiffness EAx EAy at the 4 integration points on the surface of the shell elements in an elastic element this Et z stiffness would be j PRNEISHELL Print the bending stiffness Elx Ely at the 4 integration points on the surface of the shell elements in an elastic element this Et stiffness would be _ 12 1 v PRNEIBEAM Print the stiffness EA ES and El in the beam elements Output results last line One blank line as last l
14. 083INF AL5083SUP AL7OZ0INF AL7O20SUP USER_STEEL PSTEELA16 e ELPLANESTR PLSTRVML STEELEC32D SILCONC2D CALCONC2D VMRANK2D BLPLSTRVM BLPLSTRDP Material description sub series parameters One line second line of two line material sub series INSULATION MATERIAL TYPES If CMAT INSULATION USER1 USER2 USER3 USER4 USERS X_GYPSUM C_GYPSUM no parameter is necessary because this material does not carry any stress In this case the second line is a blank line UNIAXIAL MATERIAL TYPES If CMAT ELASTIC this material is valid only at 20 C PARACOLD 1 NM Young s modulus PARACOLD 2 NM Poisson ratio If CMAT BILIN this material is valid only at 20 C PARACOLD 1 NM Young s modulus PARACOLD 2 NM Poisson ratio PARACOLD 3 NM Yield strength PARACOLD 4 NM Slope of the hardening branch gt gt gt lt 23 02 2011 36 If CMAT RAMBOSGOOD this material is valid only at 20 C PARACOLD 1 NM E Young s modulus PARACOLD 1 NM Poisson ratio PARACOLD 3 NM Ip the limit of proportionality PARACOLD 4 NM n exponent of the law PARACOLD 5 NM K factor of the law o E for o lt l E p e oe for o gt lp E K If CMAT CALCONCEC2 SILCONCEC2 PARACOLD 2 NM Poisson ratio PARACOLD 3 NM Compressive strength PARACOLD 4 NM Tensile strength PARACOLD 5 NM lt 0 if peak stress strain minimum value stiffer
15. 62 SLS1 4311 stainless steel PARACOLD 1 NM Young s modulus PARACOLD 2 NM Poisson ratio PARACOLD 3 NM Yield strength PARACOLD 4 NM Ultimate tensile strength If CMAT STEELEC3 STEELEC3EN STEE STEELEC2EN PSTEELA16 PARACOLD 1 NM Young s modulus PARACOLD 2 NM Poisson ratio PARACOLD 3 NM Yield strength PARACOLD 4 NM Maximum temperature for a reversible behaviour during cooling PARACOLD 5 NM Rate of decrease of the residual yield strength when the maximum temperature has been greater than PARACOLD 4 NM N m kK 4 HC3DC STEELEC2 If CMAT WOODECS5 23 02 2011 38 PARACOLD 1 NM Young s modulus PARACOLD 2 NM Poisson ratio PARACOLD 3 NM Compressive strength PARACOLD 4 NM Tensile strength If CMAT USER_STEEL PARACOLD 1 NM Young s modulus at 20 C PARACOLD 2 NM Poisson s ratio at 20 C PARACOLD 3 NM limit of proportionality at 20 C PARACOLD 4 NM critical temperature in C beyond which the yield strength is not fully recovered during cooling PARACOLD 5 NM the rate of decrease of the residual yield strength if the temperature has exceeded the critical temperature This USER_STEEL material has the same expression of stress strain relationship as steel of Eurocodes but it will behave at elevated temperatures according to the decreasing curves specified in the file USER_STEEL TXT that t
16. 8 SHELL elements Note This series is skipped if no SHELL element is present in the structure One line first line of possible multiple line series lt A10 gt NODOFSHELL Shell elements file list One line first part of shell element sub series one sub series for each element type lt A20 gt left justified CFILENAME CFILENAME File name where the information concerning this section type is read Note The name of the TSH files that describe the sections heated by the HASEMI fire is for each section type the name of ONE of the relevant TSH file For example sO156_3 tsh The information about the re bar layers has to be present only in this file not in the other TSH files of the same section type that describe the temperature at the other points of integration As a consequence all the shell elements of one section type have the same re bars Shell element material translation One line for each different material in section second part of shell element sub series lt A10 gt lt I5 gt lt I5 gt TRANSLATE N1 N2 N1 Local number of this material in this section type N2 Global number of this material in the structure Shell element series end of translation One line lt A10 gt ENDTRANSLA Shell element list One line for each shell element lt A10 gt lt 9 15 gt ELEM NSH N1 N2 N3 N4 ITYPESHELL NSH KGENE NSH Number of the element
17. LID elements are used to calculate the warping function and the torsional stiffness of the cross section The torsional properties obtained from this calculation are added to the results obtained from the temperature analysis of the same cross section for subsequent structural analysis In cases where the warping function is not necessary such as in the case of uniform torsion or a cross section with a warping function equal to zero and if the torsional stiffness can be found in standard tables or by analytical formula then this analysis need not be performed In such situations the torsional stiffness is simply introduced as a property of the cross section for the structural analysis 1 2 3 Structural analysis at elevated temperature For each calculation the loads are applied to the structure described as BEAM TRUSS and SHELL elements The temperature history of the structure due to fire is read from the files 23 02 2011 5 created during the temperature analysis As the computation strategy is based on a step by step procedure the following information can be obtained until failure occurs in the structure e Displacement at each node of the structure e Axial and shear forces and bending moments at integration points in each finite element e Strains stresses and tangent modulus in each mesh at integration points of each finite element 23 02 2011 6 1 3 Capabilities of SAFIR SAFIR can be used for performing three different types o
18. NDOF 1 e 2nd order component of the longitudinal displacement no other elements must be linked to this node If NDIM 3 The nodes supporting truss and solid elements must have NDOF 2 3 e translation in the global axis 1 e translation in the global axis 2 e translation in the global axis 3 The end nodes supporting beam elements must have NDOF 2 7 e translation in the global axis 1 translation in the global axis 2 translation in the global axis 3 rotation about global axis 1 rotation about global axis 2 rotation about global axis 3 warping The internal node of beam elements must have NDOF 1 e 2nd order component of the longitudinal displacement The nodes of shell elements must have NDOF 6 e translation in the global axis 1 translation in the global axis 2 translation in the global axis 3 rotation about global axis 1 rotation about global axis 2 rotation about global axis 3 END NDOF Indicates that the series is finished 23 02 2011 20 SERIES 5 optional MATRIX SOLVER 1 card optional SOLVER gt gt CHOLESKY SOLVER A6 command CHOLESKY A8 command used to force SAFIR to solve the system of equations by the method of Cholesky with a storage of the matrix by a skyline method This method is not as efficient as the default method of Pardiso based on a sparse matrix solver It is thus not recommended to use this card The possibility has been given as a safety measure because
19. NNO1 2 NNO3 1 NNO2 2 NNO3 NNO1 NT NNO3 NNO1 NT NNO3 1 NNO2 NT NNO3 Note The active nodes where the warping function has to be calculated must have NDOF 1 Two options are possible for each node where the warping function must not be calculated 1 declare that the node bears 1 D 0o F then fix it in the series 6 on FIXATIONS in the STR file see 3 4 2 2 declare that it has 0 D o F which saves times in series 6 on FIXATIONS End of series One line END _NDOF SERIES 7 Torsion One line TORSION SERIES 9 Renumbering strategy One line choice of options NORENUM No renumbering of the equations or RENUMPERM Renumbering of the equations by logical permutations or RENUMGEO NNO1 Renumbering of the equations by geometrical method NNO1 Node number where geometrical renumbering will start NNO1 0 must be typed then renumbering started successively from all the nodes or RENUM RENUMGEO RENUMPERM or READRENUM Use previous renumbering from REN file SERIES 11 Number of materials 23 02 2011 46 One line NMAT NMAT NMAT Number of different materials Note If two materials have the same material law but different characteristics it makes two different materials e g C20 and C25 concrete SERIES 12 Number of different elements One line first line of five line series ELEMENTS Number of differe
20. OCOMEBACK is chosen the simulation is stopped the first time the stiffness matrix is not positive definite If COMEBACK is chosen each time the stiffness matrix is negative time is reset at the last converged point and the simulation restarts from there with a time step divided by 2 The division of the time step goes on until the time step is smaller than TIMESTEPMIN For dynamic analysis If NOCOMEBACK is chosen the simulation is stopped the first time the left term of the equation Kg Cq M q F isnot positive If COMEBACK is chosen each time this term is negative or the number of iterations necessary to obtain the convergence is greater then 3 time is reset at the last converged point and the simulation restarts from there with a smaller time step The division of the time step goes on until the time step is smaller than TIMESTEPMIN If for three simultaneous time steps the convergence is obtained in less then three iterations the time step is multiplied by 2 limited at the value of the initial time step 23 02 2011 22 SERIES 11 optional EQUATION RENUMBERING One and only one of the following cards may be used The card may be omitted if the sparse matrix solver has been used which is the default option because renumbering is perform by Pardiso and the renumbering made by SAFIR does not accelerate the runs the time spent for renumbering is thus wasted One of these cards should be used only of CHOLESKY has been c
21. Pardiso has been introduced recently in the code this card allows going back to the previous but outdated method in case any problem would appear with the new method If this card is used the next card on NCORES cannot be used because Cholesky systematically uses only one core of the computer 1 card optional NCORES ncores gt NCORES A6 command gt ncores integer Number of cores of the CPU of the computer used by matrix solver The default value is 1 in which case this card may be omitted This card can be used to force SAFIR to use more than 1 core if present on the computer Recent experience has shown that using more than 1 core hardly reduces the time of the runs with the present version of Pardiso and this card can thus be omitted as a common practice The possibility of using the card has nevertheless been given in order to allow users to perform their own test on their particular system and in order to offer the possibility of working with more than 1 core in the future if new releases of Pardiso show to exploit several cores more efficiently This card cannot be used if the previous card of CHOLESKY has been used because Cholesky systematically uses only one core of the computer SERIES 7 Loads One line first line of three possible line series either STATIC wet or or if the structure or one part of it is submitted to the fire and a static analysis is required This is the standard option STATICCOLD ae i
22. UNIVERSITY OF LIEGE Department ArGEnCO Service Structural Engineering USER S MANUAL FOR SAFIR 2011 A COMPUTER PROGRAM FOR ANALYSIS OF STRUCTURES SUBJECTED TO FIRE by J M Franssen January 2011 jm franssen ulg ac be 23 02 2011 TABLE OF CONTENTS 1 INTRODUCTION sorol aieeaii ea AE E OEE EEL E A EEEE E cdewtose dese AEE 3 1 1 Generals E E E A E E E AEE E 3 1 2 Analysis Procedure is oisccsss ornustcorteceecaee tesa N E a Ee EE E E E EAEE AKE R 3 1 2 1 THEM Al ANALYSIS ccsssossstescissccavsvvvsscwteaceteesavsonuuues sunivesauaveassovesisacadsiubdecdsdestaiss 3 1 2 2 Analysis of torsional stiffness of BEAM elements 111ccccccccesseeserrrrneneees 6 1 2 3 Structural analysis at elevated temperature ss1cccccceeenessseenenessseenneeseees 6 1 3 Capabilities of SAFIR ccecccesccssecsseesecesecseecseeeseceneenensceesscnsecaeceaecsaecseecaeeeaeseaeseneeeeseaeecsaecaeceeeaeeeneesss 7 1 3 1 Capabilities concerning the temperature ANALYSIS 111ccccseeeersssenennesees 7 1 3 2 Capabilities concerning the torsional ANAILYSIS s 1cccsseeesssssennrssseenntesees 7 1 3 3 Capabilities concerning the structural ANALYSIS ccccceerecscseeetesseenttesnees 7 1 4 Common Features in all Analyses snasta nee ees eea a EEEE A OnE S EEI EE ENES 8 1 5 SAFIR functions and user defined functions ce ee ssseeecseeseceseeeceseceeesecseesecnesseceaeeeesaecaeeeeeaecateeeenerenenes 9 TB Geh ral prine ip E si
23. ad to a good precision estimate SERIES 22 Loading One line first line of possible multiple line series LOADS Loading function One line second line of possible multiple line series FUNCTION CFORCE NLO CFORCE NLO Function showing how the load vector NLO varies as a function of time see 1 5 2 Loading function possible multiple node loads One line added for each point load directed at a node NODELOAD NNO LOAD 1 LOAD 2 LOAD NDOF NNO Number of the node where loads are applied LOAD 1 Load at degrees of freedom 1 LOAD 2 Load at degrees of freedom 2 LOAD NNDL Load at degrees of freedom NDOF Loading on beam elements or One line added for each element with a distributed load applied DISTRBEAM NBM TRAV 1 TRAV 2 TRAV NDIM NBM Number of the specific BEAM under a distributed load TRAV 1 Uniformly distributed load in the direction of the global axis 1 TRAV 2 Uniformly distributed load in the direction of the global axis 2 TRAV NDIM Uniformly distributed load in the direction of the final global axis GDISTRBEAM NBM TRAV 1 TRAV 2 TRAV NDIM KGENE NBM Number of the specific BEAM under a distributed load TRAV 1 Uniformly distributed load in the direction of the global axis 1 TRAV NDIM Uniformly distributed load in the direction of the final global axis KGENE distributed loads are generated between the previ
24. atures are calculated from t 2 to t 2 For particular cases like for example a uniform temperature distribution a similar file can be created with a text editor The number of elements and the size here the thickness of these elements is independent from the number and position of the points of integration that will be used later in the structural analysis For the structural analysis the temperatures at the points of integration are linearly interpolated from the temperatures of the nodes THIS IS A COMMENT LINE THICKNESS 0 10 MATERIAL 1 REBARS 0 HOT POSITIONS OF THE NODES NUMBER OF POSITIONS 11 0 5000E 01 0 4000E 01 0 3000E 01 0 2000E 01 0 1000E 01 0 0000E 00 0 1000E 01 0 2000E 01 0 3000E 01 0 4000E 01 0 5000E 01 23 02 2011 4 0 0500 56 41 0 0400 25 16 0 0300 20 15 0 0200 19 96 0 0100 20 00 0 0000 20 00 0 0100 20 00 0 0200 20 00 0 0300 20 00 0 0400 20 00 0 0500 20 00 TIME 120 0000 SECONDS OR 2 MIN 0 SEC 0 0500 95 16 0 0400 41 51 0 0300 24 43 0 0200 20 54 0 0100 20 01 0 0000 20 00 0 0100 20 00 0 0200 20 00 0 0300 20 00 0 0400 20 00 0 0500 20 00 1 2 2 Analysis of torsional stiffness of BEAM elements This analysis is usually performed when analyzing structures with 3 D BEAM elements either because non uniform torsion and beam cross section were subject to warping warping function is not equal to zero or because the torsional stiffness is not available from tables or formulas The 2 D SO
25. c cae aa a aiara a aaea Sect al ets a aa aaraa ve todeucadetoedatcnes ous 9 1 5 2 SAFIR defined function S is iccsec castes sens cise cedeesueccedess use cxdevews ansia daccesbbstnteeetiest 9 1 5 3 User defined functions so secriiesssstessstuacswctssususasieotoseobsdvantuasstuduedsaiassusssioenccasne 10 1 6 Signs CONVEN ONS n aa E E E E A NR A ORRE E E E E E A 11 1 6 1 Global and localaxeS 2 ccd ste ciesshe eeeteirciesbt cree narini is anasanat 11 1 60 27 SI CSSOS sos cst ae ea rate aae aer ap a a sees eesti te nates wa Macestecacteeteds 11 Z INPUT DESCRIPTION sei cose Siecascetsslsc ects I A IA R bb cv AE AA AE ines ebb OA 12 3 DETAILED INPUT DATA AND FORMAT ccceceeccsssseescseeseseesceeceeecesecaeeaeseceenaeeecaeeaesecaeeaseeeeeeaeaeeaeeaeersees 17 3 1 Description and Format of the IN file for Thermal Analysis eceeeseeecsseseeesecseeeecneeeeceaeeeeeseeaeeaes 17 3 2 Description and Format of the eventual file describing the local HASEMI fire s for a thermal analysis 18 3 3 Description and Format of the IN file for Structural Analysis ccccceescesseesceesceesceeeceeeceeenseesaeeneeenees 18 3 4 Description and Format of the IN file for Torsional Analysis c ccccesccescceseceeceeeceeceseeeseceeeeeeseeees 45 3 5 Structure of the TEM files used with the BEAM F E eccecesesccsseseseeecseeeecneeeeceaeeeeesceaeeeesaecaeeeeeneeeres 52 3 6 Structure of the TSH files used with the shell F Eo cee eeeecsseecessecsee
26. cement variation is written at every iteration The temperatures in the fibres of the beam elements are written The velocity and acceleration are written at every time step In a dynamic analysis The out of balance forces are written at every iteration The reactions are written for at every node where at least one degree of freedom is restrained by a BLOCK or a SAME command The sum of the reactions of all nodes is also written for each degree of freedom It allows verifying the total applied load except when master slave relationships are used for the supports in which case the results may be confusing because some reactions are counted several times Print the internal forces of the beam elements Axial forces are positive in tension Bending moments calculated as M oydQ hence M is positive if Q tension prevails in the regions of the section with positive values of y 23 02 2011 43 M aM Shear forces calculated as V where M is the bending moment at the last longitudinal point of Gauss in the beam element M is the bending moment at the first longitudinal point of Gauss in the beam element and AL is the distance between these two points of Gauss Similar for M and V PRINTSOLID Print the stresses in the solid elements PRNSIGMABM NBM NG Print the stresses in a beam element NBM Number of the beam element where stresses are printed NG Integration point of the beam element
27. ction TRAV 2 only present if a 3D analysis is made KGENE Increment on the element number Distributed mass are generated between the previously defined element and the present element Mass on shell elements Self Weight or One line added for each shell element with a distributed mass applied M_SHELL NSH TRAV 1 NSH Number of the specific SHELL element under a distributed mass TRAV 1 Uniformly distributed mass on the shell element kg m GM_SHELL NSH TRAV 1 KGENE NSH Number of the specific SHELL element under a distributed load TRAV 1 Uniformly distributed mass on the shell element kg m KGENE Increment on the element number Mass end of series One last line of series END_MASS 23 02 2011 35 SERIES 24 Material description One line first line of possible multiple line series MATERIALS Material description sub series One sub series entered for each NMAT material type One line first line of two line material sub series CMAT CMAT Name of the material Valid material names are O INSULATION USER WSEIRZ USERS USER WSHIRS I CYR SUM CEN SUM e ELASTIC CALCONC_EN SILCONC_EN CALCONC_PR Seen CON GRE Ry CALCONCEC2 SKeONCHEZ LWCONCEC2 PARABCONC CALCO_COLD Sn COme OID SMEETECSI STEELE CSEN SLR E aC SIC SR LgCZ STEELEC2ZEN SLS1 4301 SLS1 4401 SLS1 4404 ShS1 4571 ShS1 4003 SLS1 4462 SLOL ASEL BILIN RAMBOSGOOD WOODEC5 AL6061T6C AL5
28. d the following lines have to be used to attach D o F to the nodes where they must be present Degrees of freedom for a series of nodes One line added for each series of nodes FROM NNO1 TO NNO2 STEP NNO3 NDOF NDOF NNO1 First node of this group of nodes NNO2 Last node of this group of nodes NNO3 Node step NDOF Number of degrees of freedom for group of nodes The nodes NNO1 NNO1 NNO3 NNO1 2xNNO3 NNO2 2xNNO3 NNO2 NNO3 NNO2 have NDOF degrees of freedom or One line added for a repeating series of nodes repeated copies get the same degrees of freedom as the original REPEAT NNO1 TO NNO2 STEP NNO3 TIME NT NNO1 First node to be repeated NNO2 Last node to be repeated NNO3 Node step NT Number of times that the nodes are to be repeated Note The command will create the following groups NNO1 NNO3 NNO1 NNO3 1 wee NNO2 NNO3 NNO1 2xNNO3 NNO1 2xNNO3 1 NNO2 2NNO3 NNO1 NTxXNNO3 NNO1 NTxNNO3 1 NNO2 NTxNNO3 23 02 2011 19 One line If NDIM 2 The nodes supporting truss and solid elements must have NDOF 2 2 e translation in the global axis 1 e translation in the global axis 2 The end nodes supporting beam elements must have NDOF 2 3 e translation in the global axis 1 e translation in the global axis 2 e rotation about virtual global axis The internal node of beam elements must have
29. d to series if truss elements are used TRUSS NTRUSS NGEOTRUSS NTRUSS Number of TRUSS elements in the structure NGEOTRUSS Number of different groups of geometrical properties Note One group of geometrical properties comprised elements that had the same materials the same cross sectional area and the same temperature history Different elements shell elements sub series One line first line of four line sub series SHELL NSHELL NGEOSHELL NSHELL Number of SHELL elements in the structure NGEOSHELL Number of different groups of geometrical properties Note One group of geometrical properties comprised elements that had the same materials the same thickness the same reinforcing bars and the same temperature history 23 02 2011 24 Different elements Shell elements sub series shell thickness One line second line of four line sub series NGTHICK NGSHELLTHICK NGSHELLTHICK Number of points of integration on the thickness of the elements Cannot be less than 2 and cannot be more than 9 Different elements shell element sub series rebar One line fourth line of four line sub series NREBARS NREBARS NREBARS Number of REBAR layers in the shell elements Last line of series END ELEM SERIES 14 The nodes One line first line of multiple line series lt A10 gt lt A10 gt NODES or NODES_CYL NODES_ CYL is used if the cy
30. er of the slave node NNO2 Number of the master node CTRAV 1 YES One line for repeating previous slave node REPEAT NUMBER INC CTRAV 1 NUMBER Number of times that the preceding SAME command must be repeated INCR Increment on NNO1 and NNO2 CTRAV 1 YES Optional line to create master slave relationships between all nodes with same coordinates SAMEALL YES All the nodes of the structure that have the same coordinates with a precision of 0 1 mm will automatically be attributed a master slave relationship Last line of series END_FIX SERIES 16 SOLID elements One line first line of possible multiple line series lt A10 gt NODOFSOLID Solid element list One line added for each solid element ELEM NE NODE 1 NE NODE 4 NE MAT EPSRSOLID KGENE NSOL Number of this element NODE 1 NE First node of this element NODE 2 NE Second node of this element NODE 4 NE Last node of this element MAT Material of this element EPSRSOLID Residual stress in this element KGENE Allows the generation from the previously defined element up to this one KGENE gives the increment on the nodes number or REPEAT NER INC NODE 2 NE NODE 4 NE MAT EPSRSOLID KGENE NER Number of elements to repeat INC Increment on the node number NODE 2 NE Any value can be 0 NODE 4 NE Any value can be 0 MAT Any value can be
31. ers starting from 1 It is necessary to indicate at the level of the structure which global material number corresponds to the numbers given in the TEM files Beam element sub series last line One line to mark end of sub series END_TRANS Beam elements list in increasing order from 1 to NBEAM ELEM NE NODOFBEAM 1 NE NODOFBEAM 4 NE ITYPEBEAM NE NE Number of this element NODOFBEAM 1 NE First end node of this element NODOFBEAM 3 NE Third i e central node of this element NODOFBEAM 2 NE Second end node of this element NODOFBEAM 4 NE 4 node of this element present only if NDIM 3 ITYPEBEAM NE The section type of this element or or a a ELEM NE NODOFBEAM 1 NE NODOFBEAM 4 NE ITYPEBEAM NE KGENE KGENE allows the generation from the previously defined element up to this one KGENE gives the increment on the first 3 nodes 23 02 2011 28 or EAT NE Nincr123 Nincr4 NincrType Ntimes Example NE The NE previously defined elements will be repeated NINCR123 increment on the nodes 1 2 and 3 NINCR4 increment on the node 4 present only if NDIM 3 NINCRTYPE increment on the type of the element NTIMES how many times these NE elements will be repeated The following sequence ELE 1 GELE 8 ELE 9 GELE 16 ELE 17 GELE 24 ELE
32. ess strain relationships in the load bearing materials are non linear and are temperature dependent In structures exposed to fire the materials are subjected to initial strains ei thermal effects em and stress related effects c The stresses are therefore caused by the difference between the total strain tota obtained from the nodal displacements and the initial and thermal strains 23 02 2011 15 2 5 Convergence Criteria In order to converge to a solution a tolerance value has to be specified in the program SAFIR uses an iterative procedure to converge on the correct solution for each increment The precision given in the data file is a small value that must be reached at different times in SAFIR calculations in order to have convergence A good precision value is dependent on the type of structure that is being analyzed and information from preliminary runs However if the user does not know which to choose a value of 0 001 can be used as a starting point In case of a dynamic analysis the default value of 0 0005 is recommended After the first run an examination in the output of the out of balance forces and increments of displacement during subsequent iterations can help the user to modify the corresponding precision value to obtain an acceptable solution 23 02 2011 16 3 DETAILED INPUT DATA AND FORMAT 3 1 Description and Format of the IN file for Thermal Analysis See Users manual of Safir Thermal docx Sect
33. f SAFIR is used to determine the ultimate load bearing capacity of a structure which is not submitted to the fire i e at room temperature DYNAMIC es if the structure or one part of it is submitted to the fire and a dynamic analysis is required 23 02 2011 21 Static staticcold and dynamic must be followed by the type of convergence procedure required during the structural analysis The program can use a pure Newton Raphson procedure PURE_NR or a modified Newton Raphson procedure APPR_NR PURE_NR is recommanded for structures made of beams and APPR_NR is recommanded for structures made of shells Load number of vectors One line second line of two line series NLOAD NLOAD NLOAD Number of load vectors One load vector is made of the load that will vary with time according to the same function SERIES 8 Inclined supports One line OBLIQUE NOBLIQUE NOBLIQUE Number of inclined supports Every node where a boundary condition is expressed in a local system of coordinates instead of the global system of coordinates of the structure is an oblique support A 0 must be typed if there is no oblique support SERIES 9 Convergence strategy One line first line of two line series choice of two possible settings COMEBACK TIMESTEPMIN TIMESTEPMIN Minimum value for the time step in case of comeback only or NOCOMEBACK Note For static analysis If N
34. f calculations namely thermal torsional and structural analysis The capabilities of the program concerning these three analysis types are outlined in this section 1 3 1 Capabilities concerning the temperature analysis Plane sections as well as three dimensional structures can be analyzed Plane sections are discretized by triangular and or quadrilateral rectangular and non rectangular elements allowing representation of virtually all cross sectional shapes Three dimensional structures are discretized by solid elements prismatic and non prismatic with 6 or 8 nodes This allows the representation of virtually all structure shapes e Variation of material from element to element is possible The fire temperature defined as a function of time can either be the standard curves predefined in the code ISO 834 ASTM E119 ULC S 101 or any other curve can be introduced through data points Cooling down phases can be considered Variation of material properties with temperatures as well as the evaporation of moisture can be considered Can analyze thermal performance of materials such as steel reinforced concrete and composite steel concrete sections Other materials can also be analyzed provided their physical properties at elevated temperatures are known 1 3 2 Capabilities concerning the torsional analysis e Allows virtually all cross section shapes to be represented Materials are considered to be
35. function e g F ISO or a file name The heat flux at the boundary will be calculated from the temperature of the fire curve T and the temperature on the surface T according to q h T T o8 T T Note F20 frontiers can be added on other surfaces e g on the upper unheated side of a slab If the user does not know the value to start with 10 is used to make a first simulation and look at the incremental displacements and out of balance forces This can give some useful information to lead to a precision estimate See series 13 Note This value is also used as a small number at different locations in SAFIR A good value depends on the type of structure that is being analyzed and the 23 02 2011 17 experience of the user If the user does not know the value to start with 10 is used to make a first simulation and look at the incremental displacements and out of balance forces This can give some useful information to lead to a precision estimate See series 13 Note Thermal conductivity specific heat and specific mass are taken from EN for STEELEC3EN and STEELEC2EN from ENV for the other steels The only difference is that for ENV steels the emissivity is divided by 0 8 in internal cavities VOIDS Note For ENV concretes the emissivity is divided by 0 8 in internal cavities VOIDS 3 2 Description and Format of the eventual file describing the
36. h Tensile strength lt 0 if peak stress strain minimum value stiffer 0 if peak stress strain recommended value gt 0 if peak stress strain s maximum value more ductile If CMAT VMRANK2D PARACOLD 2 NM PARACOLD 3 NM PARACOLD 4 NM If CMAT BLPLSTRVM PARACOLD 1 NM PARACOLD 2 NM PARACOLD 3 NM PARACOLD 4 NM If CMAT BLPLSTRDP PARACOLD 1 NM PARACOLD 2 NM PARACOLD 3 NM PARACOLD 4 NM PARACOLD 5 NM Poisson ratio Compressive strength Tensile strength Young s modulus Poisson ratio Yield strength slope of the hardening branch Young s modulus Poisson ratio Yield strength slope of the hardening branch Qa 23 02 2011 41 If CMAT NM BLPLSTRVM PARACOLD 1 NM E the Young s modulus PARACOLD 2 NM The Poisson s ratio PARACOLD 3 NM fp the limit of proportionality PARACOLD 4 NM Bi linear plane stress Von Mises material law The material is valid at room temperature If CMAT NM STEELEC3PS PARACOLD 1 NM E the Young s modulus PARACOLD 2 NM The Poisson s ratio PARACOLD 3 NM fy the limit of proportionality Non linear plane stress material law The material is the steel material according to Eurocode 3 part 1 2 SERIES 25 Time discretization One line first line of possible multiple line series TIME Time frames Two cases are possible 1 In a dynamic analysis with comeback a single time step
37. he user has to create and locate in the same folder as the input file In the file USER_STEEL TXT ke ky K and sm are given at different temperatures Between two temperatures a linear interpolation is performed by SAFIR ke ky and ky are the reduction factors at elevated temperatures relative to the values E fy and f at 20 C Eth is the value of the thermal elongation at elevated temperature Structure of the file USER_STEEL TXT One line Number_of_T NUMBER_OF_T NUMBER_OF_T number of elevated temperatures at which the values of the reduction factors are given One line Jp KE Kfy Kfp EPSth One line for each temperature added to series T ke T k T Kip T en T T Temperature at which the reduction factors are given ke T reduction factor relative to the value of E Young s modulus at 20 C kfy T reduction factor relative to the value of fy effective yield strength at 20 C kip T reduction factor relative to the value of fp limit of proportionality at 20 C Eth T thermal elongation at temperature T 23 02 2011 39 l Note To have the same thermal elongation as in the material STEELEC3EN for all temperatures the first value written in the file must be equal to 1 Example The following file describes a material that has user defined variations of the E fy and fp but the same thermal elongation as the steel of Eurocode 3 Number_of_T 4
38. hosen as the matrix solver see series 5 1 card optional gt NORENUM A7 Command No renumbering of the equations will be performed Introducing this card has the same effect as omitting this card The possibility is given to introduce this card for compatibility with earlier version of the GID SAFIR interface 1 card optional gt RENUMPERM A9 Command Renumbering of equations by logical permutations 1 card optional RENUMGEO nno1 gt gt RENUMGEO A9 Command Renumbering of equations by geometrical method nno1 integer Number of the node where geometrical renumbering will start If nno 0 then renumbering starts successively from all nodes this process can take a long time RENUMGEO nnoi with nnoi being the number of a node located geometrically in a comer of the model is probably a good compromise between the time spent for renumbering and the acceleration provided to the run in the method of CHOLESKY 1 card optional gt RENUM A4 Command Has the same effect as RENUMGEO 7 RENUMPERM Produces then most efficient renumbering but can take a very long time 1 card optional gt READRENUM A8 Command The renumbering has been done in a previous run The match between equation numbers before renumbering and equation numbers after renumbering is read from the REN file that had been created during the renumbering This card can be used only if the typology of the
39. ies lt A10 gt OUTPUT One line TIMEPRINT Timeprint frames One line second line of multiple line series TIMEPRINT UPTIMEPRINT lt A 10 gt lt G 10 0 gt TIMEPRINT Any value UPTIMEPRINT Any value Timeprint last line One line end of time discretization series END_TIMEPR Output results last line One blank line to mark end of series lt A80 gt 23 02 2011 51 3 5 Structure of the TEM files used with the BEAM F E As many lines as needed lt A80 gt Comment lines 1 blank line lt A80 gt 1 line lt A10 15 gt NF IBERBEAM NFIBERBEAM NGB of fibres in this section 1 line lt A10 gt oj FIBERS 1 line lt A10 2G10 0 gt NODELINE Series for the position of the node of the beam element in the y z system of co ordinates YO y co ordinate of the node in the y z system ZO z co ordinate of the node in the y z system 1 line YC_ZC Series for the position of the centre of rotation of the beam element in the y z system of co ordinates Yc y co ordinate of the centre of rotation in the y z system Zc z co ordinate of the centre of rotation in the y z system NFIBERBEAM lines lt 3E13 6 15 E13 6 gt RCOORDYZINBEAM 1 NFB NGB y co ordinate of this fibre RCOORDYZINBEAM 2 NFB NGB z co ordinate of this fibre FIBERSECTION NFB NGB cross sectional area of this fibre MATBEAM NFB local number of the material present in this fibre EPSRBEAM NFB NGB residual
40. in the elastic stage at ambient temperature The user may adjust the obtained torsional stiffness in order to take into account an increase of temperature during the fire The torsional stiffness remains constant during the simulation of the structural behaviour 1 3 3 Capabilities concerning the structural analysis e Plane or 3 D structures can be analyzed The structure is discretized by means of three different element types Truss elements made of one single material with one uniform temperature per element beam elements either pure steel reinforced concrete or composite steel sections and shell elements e Large displacements are considered in the truss beam and shell elements The effects of thermal strains thermal restraint can be accounted for 3 Material properties are non linearly temperature dependent e Unloading of material is parallel to the elastic loading branch Local failure of a structural member that does not endanger the safety of the whole structure can be handled by means of a dynamic analysis Nodal coordinates can be introduced in the Cartesian or cylindrical system of axes Imposed displacement prescribed degrees of freedom can be introduced 23 02 2011 7 Structures with external support inclined at an angle to the global axes can be analyzed e Residual stresses initial strains can be accounted for Pre stressed structures can be analyzed Automatic adaptation of time step is
41. ine of series 23 02 2011 44 3 4 Description and Format of the IN file for Torsional Analysis SERIES 1 Comments One line for each comment can be 0 line SERIES 2 One blank line to mark end of comments SERIES 3 Number of nodes One line NNODE NNODE NNODE Number of nodes of the section SERIES 4 Number of axes One line NDIM NDIM NDIM 2 For torsion SERIES 5 Does not exist anymore SERIES 6 Degrees of freedom One line NDOFMAX NDOFMAX NDOFMAX 1 For torsion calculations Degrees of freedom at all the nodes One line EVERY_NODE NDOF NDOF must be 1 for torsional calculations Degrees of freedom at specific nodes One line for each group of nodes with specific degrees of freedom FROM NNO1 TO NNO2 STEP NNO3 NDOF NDOF NNO1 First node of this group of nodes NNO2 Last node of this group of nodes NNO3 Node step NDOF Number of degrees of freedom for this group of nodes 0 or 1 Note The nodes NNO1 NNO1 NNO3 NNO1 2xNNO3 NNO2 2xNNO3 NNO2 NNO3 NNO2 have NDOF degrees of freedom or REPEAT NNO1 TO NNO2 STEP NNO3 TIME NT NNO1 First node to be repeated NNO2 Last node to be repeated 23 02 2011 45 NNOS Increment NT Number of times that the nodes have to be repeated Note This command will create the groups NNO1 4 NNO3 NNO1 NNO3 1 NNO2 NNO3 NNO1 2 NNO3
42. ion D 1 2 Notes 1 This series has the effect of allocating NDOF degrees of freedom D o F to all the nodes If all the nodes of the structure have the same number of D o F then the END_NDOF line finishes the series Otherwise additional lines have to be used to include the nodes which have a different number of D o F The subsequent lines do this If the line with the command EVERY_NODE is not present then all the nodes have 0 D o F and the following lines have to be used to attach D o F to the nodes where they must be present 2 The active nodes where the temperature is calculated must have NDOF 1 3 Two possible options for nodes where temperatures are not calculated e declare that a node has 1 D o F then fix it in series 6 on FIXATIONS in the STR file e declare the a node has 0 D o F This saves time in series 6 on FIXATIONS Note If NDIM 2 and the results of a thermal analysis are to be used in the structural analysis of beam elements then the first coordinate corresponds to the local y axis of the beam element and the second coordinate corresponds to the local z axis of the beam element The residual stress is meaningful only in the case of a thermal analysis made on the plane cross section of a beam the results of which will be used in a structural analysis In other cases any value can be specified preferably 0 Notes A fire curve can be a predefined
43. ir e fdt and the content of the file myfire fct would be OF 600 TAO 2400 3600 F200 10800 20 3 200 800 900 300 20s 20 for a natural fire reaching a maximum temperature of 900 C after 40 minutes and decreasing thereafter 23 02 2011 10 1 6 Sign Conventions The following sign conventions are applied 1 6 1 Global and local axes Global axes are employed when defining a structure that is to be analyzed using SAFIR This is done using the Cartesian system of coordinates For the 2 D plane problems the axes are named G1 and G2 while the local axes are named L1 and L2 Applied force and the displacements are positive in the direction of G1 and G2 the applied moments and rotations are positive in a counter clockwise direction For the 3 D problem the global axes are named G1 G2 and G3 and the local axes are named L1 L2 and L3 The movement G1 G2 G3 is dextrorsum the applied force and moments displacements and rotations are all positive in the G1 G2 and G3 directions 1 6 2 Stresses The stresses are positive in tension Axial forces obtained as a summation of the stresses are also positive in tension Bending moments in the beam elements obtained as a summation of yi oi with yi measured on the local axis L1 are positive when fibres having a positive local coordinate are in tension 23 02 2011 11 2 INPUT DESCRIPTION 2 1 Input for SAFIR For any analysis using SAFIR data files acting as i
44. le line series NODOFBEAM Beam elements file name sub series One sub series for each type of element One line first line of sub series lt A20 gt CFILENAME CFILENAME Full name of the file where the information on this section type can be found Usually the extension is TEM File name is left justified Note The name of the TEM files that describe the sections heated by the HASEMI fire is for each section type the name of ONE of the relevant TEM file For example b0017_2 tem The information about the torsion properties has to be present only in this file not in the other TEM files of the same section type that describe the temperature at the other points of integration As a consequence all the beam elements of one section type have the same torsion stiffness Beam elements sub series material translation One line added for each different material used in the section TRANSLATE MATL MATG MATL Local number of this material in this section type MATG Global number of this material in the structure Note MATL starts from 1 for the first material in this section type The second line is for the 2nd local material etc Those lines are necessary because of the strategy used for the data files One structure can be made of several BEAM section types each of them being described in one TEM file In each of those TEM files the different materials are given numb
45. lindrical system of co ordinate is chosen instead of the Cartesian system for the introduction of the co ordinates of the nodes Cylindrical input are transformed for the internal solution process by r 6 gt X r cos 0 Y r sin if NDIM 2 r 6 Z gt X r cos 0 Y r sin 0 Z if NDIM 3 Note 8 is in degrees The transformation is made after all the nodes have been read and generated CYLINDRIC is omitted if the nodes are directly input in the Cartesian system of co ordinates Nodes One line added for each node NODE NNO RCOORD 1 NNO RCOORD NDIM NNO NNO Number of the specific node RCOORD 1 NNO First global coordinate of the node NNO RCOORD NDIM NNO Last global coordinate of node NNO of NDIM global axis or GNODE NNO RCOORD 1 NNO RCOORD NDIM NNO NNO Number of the specific node RCOORD 1 NNO First global coordinate of the node NNO 23 02 2011 25 RCOORD NDIM NNO Last global coordinate of node NNO of NDIM global axis This command is used to generate equidistant nodes between the previously defined node and the current node NNO or REPEAT NNO DELTAC 1 DELTAC NDIM KGENE NNO Number of nodes to be repeated DELTAC 1 Increment on the first coordinate DELTAC NDIM Increment on the coordinate NDIM KGENE Number of times that this command has to be repeated SERIES 15 Supports and imposed displacements One line firs
46. ll tolerance value reached to have convergence A good value depends on the type of structure that is analyzed 10 may be used for the first simulation to look at the incremental displacements and if out of balance forces needs a different value SERIES 17 Material description One line first line of possible multiple line series lt A10 gt MATERIALS Material description line pair added for each different material used One line first line of two line pair lt A10 gt CMAT CMAT Name of the material Valid material names are PLASTIC BELIN 23 02 2011 50 STEELEC3 STEELEC3EN STEELEC2 STEELEC2EN PSTEELA16 CALCONC EN SELCONC EN CALCONC PR SILCONC PR Material description properties One line second line of two line pair lt G10 0 gt lt G10 0 gt lt G10 0 gt The value of the following three parameters depends on the material name introduced in CMAT If CMAT NM ELASTIC BILIN or for STEEL type materials PARACOLD 1 NM Young s modulus PARACOLD 2 NM Poisson s ratio For the CONCRETE type materials PARACOLD 2 NM Poisson s ratio PARACOLD 3 NM Compressive strength fc PARACOLD 4 NM Tension strength not used here The Young s modulus for concrete materials is calculated according to the formula E 2f 2 5x10 SERIES 18 Output results One line first line of multiple line ser
47. mitted to different fire exposures The thermal analysis is made using 2 D SOLID elements to be used later on cross sections of BEAM elements or on the thickness of SHELL elements a Temperatures in beams The temperature is non uniform in the sections of the beam but there is no heat transfer along the axis of the beams As an example a frame structure with reinforced concrete columns pre stressed main beams and structural steel secondary beams will require separate temperature analyses for each of these section types From these analyses the temperatures across the cross section are obtained and are stored for subsequent structural analysis where these sections are present b Temperatures in shells The temperature is non uniform on the thickness of the shell but there is no heat transfer in the plane of the shell The temperature analysis is performed on a section having the thickness of the shell and an arbitrary width 1 cm for example The node numbering is from 1 to NNODE 2 from the bottom to the top of the section and again from NNODE 2 1 to NNODE for the second row of nodes 23 02 2011 3 For example the Figure above has been created with the following lines for a 10 cm thick slab NODES NODE 1 0 05 0 00 GNODE 11 0 05 0 00 1 REPEAT 11 0 00 0 01 1 A TSH file is created in which the temperatures of the first NNODE 2 nodes are written Bellow is given an example of such a file Note that the temper
48. model has not been modified since the renumbering has been made SERIES 12 Number of materials One line NMAT NMAT 23 02 2011 23 NMAT Number of different materials Note If two materials have the same material law but different characteristics it makes two different materials e g S235 and S355 steel SERIES 13 Number of different elements One line first line of multiple line series ELEMENTS Different elements beam elements sub series One line added to sub series if beams are used in the structure BEAM NBEAM NGEOBEAM NBEAM Number of BEAM elements in the structure NGEOBEAM Number of different groups of geometrical properties Note One group of geometrical properties comprises elements that have the same materials the same cross section and the same temperature history One TEM file will be necessary to describe each of the NGEOBEAM groups Different elements integration points beam elements sub series One line NG NG NG Number of longitudinal points of integration in elements Cannot be less than 2 Greater than 3 is not recommended Different elements fibres of beam elements beam elements sub series One line NFIBER NFIBERBEAM NFIBERBEAM Number of longitudinal fibres in the beam elements the maximum value for all the different groups of geometrical properties Different elements truss elements One line adde
49. must be used because the program adjusts itself the time steps during calculation One single line is required TIMESTEP UPTIME TIMESTEPMAX TIMESTEP Initial time step in seconds UPTIME Time for end of the calculation TIMESTEPMAX Maximum value of the time step 2 In other cases several lines can be given maximum of IDIMTIMESTEP lines 20 in SAFIR2007 One line added for each time frame added TIMESTEP UPTIME TIMESTEP Time step in seconds UPTIME Limit of validity of this time step Time last line One line end of time discretization series ENDTIME 23 02 2011 42 SERIES 27 Thermal elongation One line choice of two options NOEPSTH If thermal elongation is not considered or EPSTH If thermal elongation is considered SERIES 28 Output results One line first line of multiple line series OUT One line TIMEPRINT PUT Timeprint frames One line added for each timeprint frame added maximum of IDIMTIMEPRINT lines TIMEPRINT UPTIMEPRINT TIMEPRINT Time step for the output of the results UPTIMEPRINT Limit of validity of this timeprint Timeprint last line One line end of time discretization series END_TIMEPR Output optional results Add one line for each option chosen PRINTDEPL PRINTTMPRT PRINTVELAC PRINTFHE PRINTREACT PRINTMN The displa
50. nal PRNNXSHELL Optional PRNEASHELL Optional PRNEISHELL Optional PRNS IGMABM lt lt Optional PRINTET lt gt lt I gt Optional PRNEPSMBM lt lt Optional PRNEIBEAM optional Blank line for end of comments 2 4 Material Properties Material names are provided in the program by command CMAT NM the values of the parameters associated with this material are introduced in the PARACOLD vector There is a maximum of eight values of PARACOLD I NM available in the program depending on the material name introduced in the CMAT NM Valid material names are e INSULATION USER1 USER2 USER3 USER4 USER5 C GYPSUM and X GYPSUM these materials have only thermal properties they do not carry any load e ELASTIC BILIN PARABCONC RAMBOSGOOD SILCO COLD and CALCO COLD these materials have only 1D mechanical properties at room temperature e STEELEC3 STEELEC3EN STEELEC3DC PSTEELA16 STEELEC2 STEELEC2EN USER _ STEEL CALCONCEC2 SILCONCEC2 LWCONCEC2 SILCONC_EN CALCONC EN SILCONC_ PR CALCONC_ PR WOODEC5 SLS1 4301 SLS1 4401 SLS1 4404 SLS1 4571 SLS1 4003 SLS1 4462 SLS1 4311 AL6061T6C AL5083SUP AL5083INF AL7020SUP and AL7020INF these materials have thermal properties and 1D mechanical properties at elevated temperatures e STEELEC32D SILCONC2D CALCONC2D ELPLANESTR PLSTRVML BLPLSTRVM BLPLSTRDP VMRANK2D these materials have 2D plane stress mechanical properties The str
51. nput files to the program are prepared For each analysis type thermal torsional or structural analysis the user prepares one data file This is an ASCII file created with a text editor in a word processor or by SafirWizard for special cases only and it must have the filetype IN This file with a IN extension contains information such as calculation strategy time discretization loads node coordinates types of finite elements used material properties etc For structural analysis the IN file specifies the name of the TEM files created during thermal and torsional analyses and in which the temperature data is stored Figure 1 shows a schematic representation of the different steps and files that may be involved in the case of a frame structure comprised of two types of different sections one for the columns and one for the beam The user must create the IN files The commands format and number of lines required for a section in the input files are briefly given in the following sections whereas the detailed structure of these files is given in Chapter 3 Thermal analysis 1 I I SafirWizard O y COLMN OU gt lt DIAMOND TEXTEDIIOR gt 77 COLUMN thermal analysis 2 firWizard gt a BEAM OUT en p BEAMIN gt AR 7 TEXTEDIOR gt o N EMM pi fo E E EO E E Mechanical analysis FRAME OUT poi TEXTEDIIOR gt gt FRAME IN
52. nt elements solid elements One line second line of five line series SOLID NSOLID NSOLID Number of SOLID elements in the section Number of points for integration One line third line of five line series NG NGSOLID NGSOLID Number of points of integration in each direction in the elements cannot be less than 1 Greater than 3 is not recommended Number of voids One line fourth line of five line series NVOID NVOID NVOID 0 Last line of series END ELEM SERIES 13 The nodes One line of multiple line series NODES or NODES_ CYL NODES _CYU is used if cylindrical coordinates are used r 6 Z and are transformed to X Y Z for the internal solution process by the formula X r cos 0 Y rsin 0 Note 8 is in degrees The transformation is made after all the nodes have been read and generated CYLINDRIC is omitted if the nodes are directly input in the Cartesian system of coordinates NODES One line added for each node described NODE NNO RCOORDG 1 NNO RCOORDG 2 NNO NNO Number of the specific node RCOORDG 1 NNO First global coordinate of the node NNO RCOORDG 2 NNO Second global coordinate of the node NNO 23 02 2011 47 or GNODE NNO RCOORDG 1 NNO RCOORDG 2 NNO NNO Number of the specific node RCOORDG 1 NNO First global coordinate of the node NNO RCOORDG 2 NNO Second global coordinate of the node NNO Thi
53. of functions 1 SAFIR defined functions These functions are embedded in the code Each function is represented by a name The comprehensive list is given here bellow 2 User defined functions If the name maximum 10 characters is not one of the SAFIR defined function SAFIR will assume that it represents the filename filetype of a file in which the user has described the evolution of the function with time by a series of time value pairs free format Linear interpolation is made between the defined points This file describing the function must be in the same folder as the input file 1 5 2 SAFIR defined functions The comprehensive list of SAFIR defined function is with tin seconds e FO f 0 e FI f 1 e FIPS f t e MOINSFIPS f t e FMOINSIPS f t e F2PM f 21t 60 e F20 f 20 e F100 f 100 e F1000 f 1000 e F1000PS f 10001 e F1PSM1000 f 0 for t lt 1000 f t 1000 for t gt 1000 e F1000THPS f t 1000 e FLOAD f t 20 for t lt 20 f l for t gt 20 e FISO f 20 345 logio 8 t 60 1 e FISOO f 345 logio 8 t 60 1 e HYDROCARB f 20 1080 1 0 325 e197 _ 0 675 e 5 9 23 02 2011 9 e ASTME119 1 5 3 f defined by linear interpolation between a set of time temperature pairs with time in minutes Temp User defined functions An example of user defined function could be e my F
54. ously defined element and the present element 23 02 2011 33 Loading on shell elements One line added for each element with a distributed load applied DISTRSH NSH TRAV 1 TRAV 2 TRAV 3 NSH Number of the specific SHELL element under a distributed load TRAV 1 Uniformly distributed load in the direction of the global axis 1 TRAV 2 Uniformly distributed load in the direction of the global axis 2 TRAV 3 Uniformly distributed load in the direction of the global axis 3 or GDISTRSH NSH TRAV 1 TRAV 2 TRAV 3 KGENE NSH Number of the specific SHELL element under a distributed load TRAV 1 Uniformly distributed load in the direction of the global axis 1 TRAV 2 Uniformly distributed load in the direction of the global axis 2 TRAV 3 Uniformly distributed load in the direction of the global axis 3 KGENE Increment on the element number Loading end of series One last line of series END_LOAD SERIES 23 Mass characteristic Notes 1 This series is present ONLY IF DYNAMIC HAS BEEN CHOSEN 2 In SAFIR masses and forces are totally independent The masses introduced produce no force and the forces are not linked to any mass As a consequence if a force of X Newton is produced by gravity a mass of X 10 kg must normally be also introduced in the data if a force is produced by wind no mass has to be introduced One line first line of possible multiple line series MASS Concentrated mass on nodes
55. perature of the slab across its thickness The positions of these nodes only depends on the discretisation which was chosen when the temperature distribution was calculated It is independent of the location of the integration points across the thickness which will be used in the structural analysis 23 02 2011 55 1 line position o position o etc the first node the one with the smallest z co ordinate the second node FH Fh position of the lest node the one with the highest z co ordinate Series 7 temperatures Repeat this group of lines for each time step 1 blank line 1 line T IME TIME value of the time when the temperatures are given Number_of_ position lines position of the node same as in series 6 temperature at this node 23 02 2011 56 3 7 Structure of the temperature files used with the truss F E As many lines as necessary each line being in a free format a pair of values in the form TIME TEMPERATURE Example 0 20 300 600 600 800 1200 1000 1500 900 1800 20 3600 20 23 02 2011
56. possible and structural calculation continues until failure This means that there is no deflection criterion to actually make the failure point 1 4 Common Features in all Analyses The common features in all computations are listed as follows Optimization of the matrix in order to reduce the computer storage and calculation time can be performed by the program using internal re numbering of the system equations This re numbering is transparent to the user The same temperature or the same displacement can be imposed at two different nodes by the use of master slave relations e Thermal and mechanical properties of the steel and concrete according to Eurocodes 2 3 and 4 are embedded in the code and can be used directly e Graphic pre processing and post processing capabilities are by the SAFlRwizard and DIAMONDXL codes respectively When needed SAFIR could be adapted so as to give the results in a format compatible with commercial graphic software such as I DEAS 23 02 2011 8 1 5 SAFIR functions and user defined functions 1 5 1 General principle In different locations of the IN file some functions of time can be introduced They are used either to describe the evolution of the gas temperature in case of a thermal analysis or to prescribe the evolution of the solution in different nodes and degrees of freedom either be it a displacement a temperature or a value of the warping function There are two different types
57. s at node NNO 1 for the D o F 1 NO otherwise CTRAV NDOFMAX YES If the solution is the same as at node NNO2 and as at node NNO1 for the D o F NDOFMAX NO otherwise or one line added for repeating series of slave node nodes REPEAT NUMBER INCR CTRAV 1 CTRAV NDOFMAX 23 02 2011 26 NUMBER Number of times that the preceding SAME command must be repeated INCR Increment on NNO1 and NNO2 CTRAV 1 YES If the solution is the same as at node NNO2 as at node NNO1 for the D o F 1 NO If there is no master slave relation for this D o F CTRAV NDOFMAX YES If the solution is the same as at NNO2 as at NNO1 for the last D o F NO If there is no master slave relation for this D o F Or one line to create master slave relationships between all nodes with same coordinates SAMEALL CTRAV 1 CTRAV NDOFMAX All the nodes of the structure that have the same coordinates with a precision of 0 1 mm will automatically be attributed a master slave relationship CTRAV 1 YES If the solution is the same for the D o F 1 NO otherwise CTRAV NDOFMAX YES If the solution is the same for the D o F NDOFMAX NO otherwise Last line indicating that the series is finished END_ FIX 23 02 2011 SERIES 16 BEAM elements Note This series is skipped if no BEAM element is present in the structure One line first line of possible multip
58. s command is used for automatic equidistant generation between the previously defined node and node NNO or REPEAT NNO DELTAC 1 DELTAC 2 KGENE NNO Number of nodes to be repeated DELTAC 1 Increment on the first coordinate DELTAC 2 Increment on the 2nd coordinate KGENE Number of times that this command has to be repeated irst coord y 2nd coord z NDIM 2 Figure 2 Coordinate order Note The first coordinate corresponds to the local y axis and the second coordinate corresponds to the local z axis of the beam element SERIES 14 Torsional centre One line first line of two line series lt A10 gt lt 5b gt lt G10 0 gt lt G10 0 gt NODELINE Yo Zo Yo First global coordinates of the node line which joins the beam elements Zo Second global coordinate of the node line Torsional centre One line second line of two line series YC_ZC Yc Zc Yc First global coordinate of the centre of torsion Zc Second global coordinate of the centre of torsion SERIES 15 Supports and imposed displacements One line first line of possible multiple line series FIXATIONS One line added for every node where no solution is to be calculated BLOCK NNO FO NNO Node number where no solution is calculated for example lines of symmetry One line added for each slave node described SAME NNO1 NNO2 CTRAV 1 23 02 2011 48 NNO1 Numb
59. s element ELEM NTR NODOFTRUSS 1 NTR NODOFTRUSS 2 NTR IGEOTRUSS NTR KGENE NTR Number of the element NODOFTRUSS 1 NTR First node of this element NODOFTRUSS 2 NTR Second node of this element IGEOTRUSS NTR Number of the section type for this element KGENE Allows for automatic generation SERIES 20 0 Oblique supports One line for each oblique support inclin Ni Nj if NDIM 2 2D structure inclin Ni Nj Nk if NDIM 3 3D structure Ni is the node where a boundary condition is expressed in a local system of coordinates Nj Nk _ are 2 other nodes of the structure Ni and Nj for a 2 D structure or Ni Nj and Nk for a 3D structure define the plane in which the node Ni can move It cannot move perpendicularly to this plane One line to indicate that this is the end of the Series 10 0 lt A10 gt END INCLIN 23 02 2011 32 SERIES 21 Precision Note One line PRECISION PRECISION PRECISION Small value that must be reached for convergence This value is also used as a small number at different locations in SAFIR A good value depends on the type of structure that is being analyzed and the experience of the user If the user has no idea of the value to start with try 10 5 10 in case of dynamic analysis then make a first simulation and look at the displacement and Out of Balance Forces see SERIES 18 This can give some useful information that could le
60. secseeeeceeeeecsseceeesecsecaeseeeevereaeeaes 54 3 7 Structure of the temperature files used with the truss F E ccccceccsseesseesceeseeesceeeceeeeeeeseeeeeseesaeesteeaes 57 List of Figures Figures Ie files anid Steps saci hates veda ones eck a seston sneecees Han eG saath tach tata e tesa Tea ceck hace Ea 12 Figure 7 Coordinate Order iscsi titi Savin eho eco sciba ta iia a a a aed eee eaten bes 48 1 INTRODUCTION 1 1 General SAFIR is a special purpose computer program for the analysis of structures under ambient and elevated temperature conditions The program which is based on the Finite Element Method FEM can be used to study the behaviour of one two and three dimensional structures The program SAFIR was developed at the University of Li ge Belgium and is today viewed as the second generation of structural fire codes developed in Li ge the first generation being another computer program called Computer Engineering of the Fire design of Composite and Steel Structures CEFICOSS As a finite element program SAFIR accommodates various elements for different idealization calculation procedures and various material models for incorporating stress strain 23 02 2011 2 behaviour The elements include the 2 D SOLID elements 3 D SOLID elements BEAM elements SHELL elements and TRUSS elements The stress strain material laws are generally linear elliptic for steel and non linear for concrete The analysis procedure
61. t line of possible multiple line series FIXATIONS Supports and imposed displacements fixed blocks One line for each node where solution follows a defined function of time and the reaction must be calculated BLOCK NNO CBLOCK 1 NNO CBLOCK NDOFMAX NNO NNO Number of the specific node where the solution must not be calculated CBLOCK 1 NNO Function describing displacement for first D o F at this node with respect to time Type NO if the displacement is not prescribed for this DoF CBLOCK 2 NNO Function describing displacement for second D o F at this node with respect to time Type NO if the displacement is not prescribed for this DoF CBLOCK NDOFMAX NNO Function describing displacement for last D o F at this node with respect to time Type NO if the displacement is not prescribed for this DoF Note For each degrees of freedom NDL from 1 to NDOFMAX CBLOCK NDL NNO is either NO if the displacement is not imposed at this D o F or the name of the function describing the evolution of the displacement at this node with respect to time FO is a common function used to model a fixed support Supports and imposed displacements slave nodes One line added for each slave node SAME NNO1 NNO2 CTRAV 1 CTRAV NDOFMAX NNO1 Number of the specific slave node NNO2 Number of the master node CTRAV 1 YES If the solution is the same as at node NNO2 and a
62. truss elements lt 6 15 gt Nodes of truss elements Go RECISION k LOADS FUNCTION NODELOAD lt 110 gt lt 6 G10 0 gt Optional multiple lines possible DISTRBEAM lt I10 gt lt NDIM G10 0 gt lt I10 gt Optional DISTRSH lt I10 gt lt NDIM G10 0 gt lt I10 gt Optional DISTRSOLID lt IL0 gt lt NDIM G10 0 gt lt I10 gt Optional END LOAD line for end of section x MASS Optional only for dynamic analysis 5 M_NODE Optional M_BEAM Optional x M_SHELL Optional END MASS line for end of section Blank line for end of comments MATERIALS lt A10 gt lt I5 gt Material name Number of temperatures lt 8 G10 0 gt Material properties multiple name properties pairs possible w TIME TIMESTEP lt G10 0 gt lt G10 0 gt Multiple lines possible ENDTIME hi NOEPSTH OR EPSTH OUTPUT Optional TIMEPRINT lt G10 0 gt lt G10 0 gt Multiple lines possible END_TIMEPR PRINTDEPL Optional PRINTTMPRT Optional PRINTFHE Optional PRINTREACT Optional PRINTMN Optional PRINTSOLID Optional 23 02 2011 14 PRINTVELAC Optional PRNSIGMASH Optio

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