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Runstream - Shell Buckling

1. 1 0 1500000E 01 4051013 0 1080000E 08 0 1080000E 08 0 3330000 0 2500000E 03 0 0 1 600000 lt m m mm B B 5 1 1 000000 100000 0 1 2 0 000000 10000 00 0 000000 10000 00 H 3 UY Tt TTT 47 HY 47 HUY HUY 47 47 c r rrr NUNNU X gt X gt X gt 47 X gt NN NUNNU xp XY X X HX X UY X X X Y NMESH no of node points 5 min 98 max NTYPEH control integer 1 or 2 or 3 for nodal point spacing REFERENCE SURFACE GEOMETRY FOLLOWS NSHAPE indicator 1 2 or 4 for geometry of meridian R1 radius at beginning of segment see p P7 Z1 axial coordinate at beginning of segment R2 radius at end of segment 22 axial coordinate at end of segment IMPERFECTION SHAPE FOLLOWS IMP indicator for imperfection 0 1 some REFERENCE SURFACE LOCATION RELATIVE TO WALL NTYPEZ control 1 or 3 for reference surface location ZVAL distance from leftmost surf to reference surf Do you want to print out r s r s etc for this segment DISCRETE RING INPUT FOLLOWS NRINGS number max 20 of discrete rings in this segment K elastic foundation modulus e g lb in 3 in this seg TEMPERATURE INPUT FOLLOWS Do you want general information on loading NTSTAT number of temperature callout points along meridian PRESSURE INPUT FOLLOWS NPSTAT number of meridional callouts for pressure LINE LOAD INPUT FOLLOWS LINTYP control for line loads or disp 0 none 1 some SHELL WALL CONSTRUCTION
2. 1 600000 Do you wish to include plasticity in this segment y y Do you wish to include creep in this segment n n Shell wall layer no 1 A stress strain curve the material of this layer must be provided by you if the same material has not appeared in a previous layer of this segment or in the shell wall of a previous shell segment Note that you must provide a stress strain curve here even if the same material has been specified previously for a discrete ring segment Is this a new shell wall material n n Do you want to have C i j printed for this segment n n Want to add more structural segments y Which segment is this 3 Are you adding to or checking an existing file n NMESH no of node points 5 min 98 max 7 NTYPEH control integer 1 or 2 or 3 for nodal point spacing 3 Geometry of the current segment NSHAPE indicator 1 2 or 4 for geometry of meridian 1 1 R1 radius at beginning of segment see p P7 4 882 4 882000 21 axial coordinate at beginning of segment 182 0 1820000 R2 radius at end of segment 4 882 4 882000 22 axial coordinate at end of segment 271 0 2710000 Imperfection geometry IMP indicator for imperfection 0 none 1 some 0 0 NTYPEZ control 1 or 3 for reference surface location 3 3 ZVAL distance from leftmost surf to reference surf 015 0 1500000E 01 Do you want to print out r s r s etc for this segment n n NRINGS number max 20 of dis
3. ITERATIONS HAVE EIGENVALUE ITERATIONS HAVE EIGENVALUE CONVERGED FOR EIGENVALUE NO 1 1 93669E 03 7 CIRCUMFERENTIAL CONVERGED FOR EIGENVALUE NO 1 1 79806E 03 8 CIRCUMFERENTIAL CONVERGED FOR EIGENVALUE NO 1 1 71769E 03 9 CIRCUMFERENTIAL CONVERGED FOR EIGENVALUE NO 1 1 68283E 03 10 CIRCUMFERENTIAL CONVERGED FOR EIGENVALUE NO 1 1 68370E 03 11 CIRCUMFERENTIAL CONVERGED FOR EIGENVALUE NO 1 1 71289E 03 12 CIRCUMFERENTIAL CONVERGED FOR EIGENVALUE NO 1 1 76469E 03 13 CIRCUMFERENTIAL CONVERGED FOR EIGENVALUE NO 1 1 83455E 03 14 CIRCUMFERENTIAL CONVERGED FOR EIGENVALUE NO 1 1 91879E 03 15 CIRCUMFERENTIAL CONVERGED FOR EIGENVALUE NO 1 2 01424E 03 16 CIRCUMFERENTIAL CONVERGED FOR EIGENVALUE NO 1 2 11815E 03 17 CIRCUMFERENTIAL CONVERGED FOR EIGENVALUE NO 1 2 22801E 03 18 CIRCUMFERENTIAL CONVERGED FOR EIGENVALUE NO 1 2 34147E 03 19 CIRCUMFERENTIAL CONVERGED FOR EIGENVALUE NO 1 2 45634E 03 20 CIRCUMFERENTIAL WAVES WAVES WAVES WAVES WAVES WAVES WAVES WAVES WAVES WAVES WAVES WAVES WAVES WAVES k k k k k k k k k k k k k k k k k k k k k k kck k k k k k k kk kk k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k ko kk kk MINIMUM BUCKLING LOAD CORRESPONDS TO N 10 CIRCUMFERENTIAL WAVES BUCKLING LOAD IS GREATER THAN
4. cases no creep all loads varying proportionally and generally increasing until bifurcation buckling or collapse occurs it is advisable to identify time directly with load and time increment with load increment Hence whenever possible the loading functions of time should be set equal to the time f time time In this way you will be able to read the load directly from the output TIME will be the same as load Please refer to pp P30 P31 for examples IUTIME control for time increment 0 or 1 IUTIME h 0 means time increment varies during case 1 means time increment is constant during case Please see the examples on pp P30 P31 and pp P61 P63 For most cases except perhaps those involving creep you will want to set IUTIME 1 IUTIME control for time increment 0 or 1 IUTIME 1 1 DTIME time increment h See the discussion on pp P30 P31 If you have a situation in which all loads are being increased in proportion then it is best to set the time increment equal to the increment of what you feel to be the most important load component of the case e g external pressure increment For example if you think a shell will collapse at about 100 psi then you might wish to reach 100 psi in 10 psi increments The time increment DTIME you would then set equal to 10 For most cases DTIME doesn t signify a real time increment TIME in BOSOR5 is just a convenient parameter to use for provision of applied loads
5. 3 for list output h IPRINT 1 means prebuckling states listed for selected time steps IPRINT 2 means buckling modes printed for selected circumferential wave numbers IPRINT 3 means both prebuckling states and buckling modes printed for selected time steps and selected circumferential wave numbers IPRINT control 1 or 2 or 3 for list output 2 2 IPLOT control 0 or 1 or 2 or 3 for plot output h IPLOT 0 means no plots at all IPLOT 1 means prebuckling states plotted for selected time steps IPLOT 2 means buckling modes plotted for selected circumferential wave numbers IPLOT 3 means prebuckling states and buckling modes plotted for selected time steps and selected circumferential wave numbers IPLOT control 0 or lor 2 or 3 for plot output 2 2 NLAST plot options 1 O0 geometry l u v w h NLAST 1 means no plotting 0 means plots of undeformed and deformed geometry only 1 means plots of geometry and u v w vs arc length NLAST plot options 1 O0 geometry 1 u v w 0 0 Do you want to plot the discretized model y y Your structure may contain segments that are very short compared to the whole model being analyzed here This detail will not show up well in plots of the entire undeformed and deformed structure Therefore you may wish to get expanded plots of these regions Please identify these regions by segment number and give a magnification factor for each region
6. HY HUY 47 HY 47 HY HY HY 47 HY HY HY HY HH HY HY 47 HH HY HY X X Y X Y NSEG number of shell segments less than 95 SEGMENT NUMBER 1 1 1 1 1 1 1 1 NODAL POINT DISTRIBUTION FOLLOWS NMESH no of node points 5 min 98 max NTYPEH control integer 1 or 2 or 3 for nodal point spacing REFERENCE SURFACE GEOMETRY FOLLOWS NSHAPE indicator 1 2 or 4 for geometry of meridian R1 radius at beginning of segment see p P7 21 axial coordinate at beginning of segment R2 radius at end of segment 22 axial coordinate at end of segment IMPERFECTION SHAPE FOLLOWS IMP indicator for imperfection 0 1 some REFERENCE SURFACE LOCATION RELATIVE TO WALL NTYPEZ control 1 or 3 for reference surface location ZVAL distance from leftmost surf to reference surf Do you want to print out r s r s etc for this segment DISCRETE RING INPUT FOLLOWS NRINGS number max 20 of discrete rings in this segment K elastic foundation modulus e g lb in 3 in this seg TEMPERATURE INPUT FOLLOWS Do you want general information on loading NTSTAT number of temperature callout points along meridian PRESSURE INPUT FOLLOWS NPSTAT number of meridional callouts for pressure NTYPE control for meaning of loading callout 2 z 3 r Z I axial coordinate of Ith loading callout z 1 Z I axial coordinate of Ith loading callout z 2 PN J normal pressure at meridional callout pt no 1 PN J no
7. Note that the magnification factor must be an integer The center of the expanded plot will be at the first point of the segment so identified The extent of structure plotted will of course depend on the magnification factor you choose Are there any regions for which you want expanded plots n n Selection of buckling modes follows NMODES quantity of buckling modes to be listed plotted h One mode circumferential wave number You rarely need to see all of the modes calculated by the main processor the critical mode is the most important of course NMODES quantity of buckling modes to be listed plotted 1 1 NTHMOD i ith mode calculated in last main run i 1 h Use the order in which the modes were calculated in the last run of the BOSOR5 main processor as a guide here not the number of circumferential waves For example if modes for circ waves n 5 10 15 20 were calculated in that order and you want to list and or plot the modes corresponding ton 5 and 15 then set NTHMOD 1 1 first mode calculated and NTHMOD 2 3 third mode calculated NTHMOD i ith mode calculated in last main run i 1 6 6 NWAVE i no of circ waves in the ith mode i 1 h In the above example NWAVE 1 5 and NWAVE 2 15 NWAVE i no of circ waves in the ith mode i 1 10 10 Do you want buckling modal output for all the segments y 2 Next give the command BOSORPOST end of the interactive POSTS
8. THAT SPECIFIED IN TIME STEP NUMBER 1 k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k k lt k k k k k k k k k k k k k k k k k k k k ck lt lt k k k k k k k lt lt kk k k k k k k k k k k k k k k k k k k k k k k k k k k k k k lt lt kk Compare the BOSOR5 prediction ITERATIONS HAVE CONVERGED FOR EIGENVALUE NO 1 EIGENVALUE 1 68283E 03 10 CIRCUMFERENTIAL WAVES with that from BIGBOSOR4 listed as follows in the file bigbosor4 case bigbosor4 runstream EIGENVALUES AND MODE SHAPES EIGENVALUE CIRC WAVES 4 1833E 02 2 1 9615E 03 4 2 1497 03 6 1 7981 03 8 1 6828E 03 10 lt local minimum from BIGBOSOR4 1 7129 03 12 1 8346 03 14 2 0142 03 16 2 2280 03 18 2 4563 03 20 3 In specifying the range of circumferential numbers to be covered in the bifurcation buckling analysis we deliberately excluded values near N 2 crcumferential waves Therefore we are capturing only one of the 2 minima contained in the complete range of N just listed from the BIGBOSOR4 runstream Next we wish to run the BOSOR5 post processors POSTSETUP and BOSORPOST First we conduct the interactive session POSTSETUP bush gt postsetup Please enter case name 1 Are you correcting adding to or checking an existing file n n Interactive input for BOSOR5 postprocessor IPRINT control 1 or 2 or
9. factor j 2 10000 10000 00 How many segments are there in the structure 3 3 Four kinds of constraint conditions exist in BOSOR5 1 constraints to ground e g boundary conditions 2 juncture compatibility conditions 3 regularity conditions at poles where radius r 0 4 constraints to prevent rigid body displacements See the figs on p P67 for example There is a constraint to ground boundary condition at Seg 8 Point 8 there are several juncture conditions e g Seg 2 Pt 1 is connected to Seg 1 Pt 9 there are several poles e g Seg 1 Pt 1 Note that if a shell is not anywhere attached to ground such as is the case for the example shown on p P75 you must choose a node at which to prevent rigid body motion You must choose this node in the section below where you are asked about constraints to ground In a section following the constraints to ground section you will be asked to provide specific data for preventing rigid body motion Types of rigid body motion are shown on p P73 An example of appropriate input data is listed on p P75 bottom CONSTRAINT CONDITIONS FOR SEGMENT NO ISEG 1 Number of poles places where r 0 in SEGMENT 0 0 At how many stations is this segment constrained to ground 1 INODE ada point number of constraint to ground INODE 1 1 E usa sss displacement constraint 0 or 1 or 2 1 IVSTAR t displacement 0 free 1 constrained 0 inr displacement 0 free l
10. more information on INDIC N for no more 0 IDEFORM indicator 0 or 1 for type of plasticity theory 1 ICPRE control 0 or 1 for type of eigenvalue problem n Do you want to reverse the rate of loading 0 KSTEP starting time step number 2 KMAX maximum less than 49 time step number 5 MAXTRL maximum number of trials at each load level 6 ITMAX maximum number of Newton iterations for each trial 0 ITIME control 0 or 1 for time increments n Do you wish to force the material to remain elastic 6 NOB starting number of circ waves buckling analysis 5 NMINB minimum number of circ waves buckling analysis 20 NMAXB maximum number of circ waves buckling analysis 1 INCRB increment in number of circ waves buckling 0 TIME starting time need not be zero in initial run y Do you want stations where plastic flow occurs listed ALUMINUM FRAME BUCKLING INDIC analysis type indicator 0 or 2 or 3 INDIC 2 Type HELP or H for more information on INDIC N for no more n IDEFORM indicator 0 or 1 for type of plasticity theory 0 ICPRE control 0 or 1 for type of eigenvalue problem 1 Do you want to reverse the rate of loading n KSTEP starting time step number 0 KMAX maximum less than 49 time step number 2 MAXTRL maximum number of trials at each load level 5 ITMAX maximum number of Newton iterations for each trial 6 ITIME control 0 or 1 for time increments 0 Do you wish t
11. that vary nonproportionally during a case In cases involving creep TIME is real time of course DTIME time increment 1 0 1 000000 TMAX maximum time to be encountered during this case h As with DTIME you associate TMAX with the most important load component and set it equal to the largest value of that load component that could possibly be of any interest at all Overestimate here For example if you think the shell you are studying might collapse at 100 psi use TMAX of about 10000 or 100000 TMAX maximum time to be encountered during this case 100000 100000 0 Next specify the various time functions associated with the loads on the structure These are the fi time to which the pointers ISTEP IDTEMP etc point NFTIME number of different functions of time h For example you may have a case involving a temperature distribution which is constant with time and a pressure distribution which varies linearly with time In such a case NFTIME 2 since there are two functions of time one function the temperature a constant and the other the pressure a varying quantity See example p P30 NFTIME must be equal to the highest value of any of the pointers IDTEMP ISTEP ISTEP1 ISTEP2 ISTEP3 which were specified in the sections on temperature and loading input See page P38 for IDTEMP p P44 for ISTEP p P46 for ISTEP1 ISTEP2 ISTEP3 NFTIME number of different functions of time 1 1 Next please provi
12. working directory the following files rw r r 1 bush bush 4209 Feb 19 09 41 1 SEG1 rw r r 1 bush bush 2948 Feb 19 09 47 1 SEG2 rw r r 1 bush bush 2948 Feb 19 09 54 1 SEG3 rw r r 1 bush bush 4680 Feb 19 10 14 1 SEG4 The command ASSEMBLE assemble concatinates these four files bush gt assemble Please enter case name 1 How many segments in the model excluding global data 3 1 SEG1 assembled into 1 ALL 1 SEG2 assembled into 1 ALL 1 SEG3 assembled into 1 ALL 1 SEG4 assembled into 1 ALL All segment files have been assembled Now give the command BOSORREAD eee END OF ASSEMBLE There now exist in the working directory the following files rw r r 1 bush bush 14760 Feb 19 10 23 1 ALL rw r r 1 bush bush 4209 Feb 19 09 41 1 SEG1 rw r r 1 bush bush 2948 Feb 19 09 47 1 SEG2 rw r r 1 bush bush 2948 Feb 19 09 54 1 SEG3 rw r r 1 bush bush 4680 Feb 19 10 14 1 SEG4 The file 1 ALL contains valid input data for the BOSORREAD processor of BOSOR5 l ALL file generated from the above run stream ALUMINUM FRAME BUCKLING 5 218000 0 000000 5 218000 0 4530000 H 0 H 3 0 0 H 2 2 0 000000 0 4530000 1 000000 1 000000 0 0 1 n 1 y 1 0 1820000 4051013 0 1080000E 08 0 1080000E 08 0 3330000 0 2500000E 03 0 0 1 600000 y n y AU AY HUY HY HUY HUY HY HUY HUY HUY HY HY HY HY HY HY H3 HY HY HY HUY HY
13. 0 SM i mass density e g alum 00025 lb sec 2 in 4 SM 1 00025 0 2500000E 03 ALPHA1 i coef thermal exp in merid direction ALPHA1 1 0 0 ALPHA2 i coef thermal exp in circ direction ALPHA2 1 0 0 EPSALW i maximum allowable eff strain percent EPSALW 1 1 6 1 600000 Do you wish to include plasticity in this segment y y Do you wish to include creep in this segment n n Shell wall layer no 1 A stress strain curve the material of this layer must be provided by you if the same material has not appeared in a previous layer of this segment or in the shell wall of a previous shell segment Note that you must provide a stress strain curve here even if the same material has been specified previously for a discrete ring segment Is this a new shell wall material n n Do you want to have C i j printed for this segment n n Want to add more structural segments n Have you supplied data for all structural segments Please answer Y or N y Next give global input and input for constraint conditions Do you want to supply these data now Y or N y How many segments in the structure 3 3 Are you correcting adding to or checking an existing file n n Next provide data which pertain to the entire structure such as time variation of loads boundary conditions and junction conditions Do you want information on time functions for loading y y Data for time variation of loads is next In common
14. 00 mdumumuugsgsosF4 UY TT TT 47 HY 47 HUY HUY 47 47 HY 47 Xr 47 4 4 47 47 47 4 47 47 4 4 47 4 XY XY XY UY X HY HY UY X X X Y number of points s s curve layer 1 NITEG no integration pts thru thickness layer no 1 Do you want to use power law for stress strain curve EPS i strain coordinates of s s curve EPS 1 EPS i strain coordinates of s s curve EPS 2 SIG i stress coordinates of s s curve SIG 1 SIG i stress coordinates of s s curve SIG 2 Do you want to have C i j printed for this segment END OF DATA FOR THIS SEGMENT SEGMENT NUMBER 2 2 2 2 2 2 2 2 NODAL POINT DISTRIBUTION FOLLOWS NMESH no of node points 5 2min 98 max NTYPEH control integer 1 or 2 or 3 for nodal point spacing REFERENCE SURFACE GEOMETRY FOLLOWS NSHAPE indicator 1 2 or 4 for geometry of meridian R1 radius at beginning of segment see p P7 21 axial coordinate at beginning of segment R2 radius at end of segment 22 axial coordinate at end of segment IMPERFECTION SHAPE FOLLOWS IMP indicator for imperfection 0 1 some REFERENCE SURFACE LOCATION RELATIVE TO WALL NTYPEZ control 1 or 3 for reference surface location ZVAL distance from leftmost surf to reference surf Do you want to print out r s r s etc for this segment DISCRETE RING INPUT FOLLOWS NRINGS number max 20 of discrete rings in this segment K elastic foundat
15. AL CONVERGED FOR EIGENVALUE NO 1 2 45634E 03 20 CIRCUMFERENTIAL k k k k k k k k k k k k k k k k k k k k k k k k k k k k k lt lt lt lt lt k k k k k k k k k k k k k k k k k k k k k k k k k k k k k lt lt kk k k k k k k k k k k k k k k k k k k k k k k k k k k ck k k k lt lt kk MINIMUM BUCKLING LOAD CORRESPONDS TO N WAVES WAVES WAVES WAVES WAVES WAVES WAVES 10 CIRCUMFERENTIAL WAVES BUCKLING LOAD IS GREATER THAN THAT SPECIFIED IN TIME STEP NUMBER 1 k k k k k k k k k k k k k k k k k k k k k k ck k k k k k k lt lt kk k k k k k k k k k k k k k k k k k k k k k k k k k k k k k lt lt kk k k k k k k k k k k k k k k k k k k k k k k kck k k ck k ko kk kk 1 CALCULATIONS BEGIN FOR TIME STEP NUMBER 1 0 00000000E 00 CURRENT TIME INCREMENT PRESSURE MULTIPLIER KKKKK TEMPERATURE MULTIPLIER AMPLITUDES BY DISTRIBUTIONS GIVEN FOR EACH SEGMENT 0 TIME SEGMENT 1 2 0 3 0 00000000E 00 0 00000000E 00 00000000E 00 0 00000000E 00 00000000E 00 0 00000000E 00 0 00000000E 00 MULTIPLY THESE TIME STEP NO 1 TIME 0 000E 00 N 10 CIRCUMFERENTIAL WAVES STABILITY DETERMINANT 2 647E 07 10 470 TIME STEP 1 NO OF NEGATIVE ROOTS 9 NO OF LAGRANGE MULTIPLIERS 9 1 CALCULATIONS BEGIN FOR TIME STEP NUMBER 2 TI
16. E 06 10 470 TIME STEP 2 NO OF NEGATIVE ROOTS 9 NO OF LAGRANGE MULTIPLIERS PLEASE READ THE FOLLOWING IMPORTANT NOTICE xk x PLEASE READ THE FOLLOWING IMPORTANT NOTICE x PLEASE READ THE FOLLOWING IMPORTANT NOTICE PLEASE READ THE FOLLOWING IMPORTANT NOTICE THE USER HAS CHECKED FOR BIFURCATION BUCKLING LOADS FOR N 6 CIRCUMFERENTIAL WAVES IT HAS BEEN DETERMINED BY THE ABOVE CALCULATIONS THAT FOR N 6 THE STABILITY DETERMINANT DOES NOT CHANGE SIGN IN THE TIME AND LOAD RANGE SPECIFIED FOR THIS RUN HOWEVER IT MAY HAPPEN THAT THE MINIMUM NONSYMMETRIC BIFUR CATION BUCKLING LOAD CORRESPONDS TO A DIFFERENT VALUE OF N THAN THE PURPOSE OF THE FOLLOWING CALCULATIONS IS TO DETER MINE FOR WHICH N THE CRITICAL LOAD IS SMALLEST A SEQUENCE OF EIGENVALUE PROBLEMS K1 N LAMBDA K2 N Q 0 IS THEREFORE SET UP WHERE K1 N STABILITY STIFFNESS MATRIX CORRESPONDING TO A BUCKLING MODE WITH N CIRC WAVES FOR THE STRUCTURE AS LOADED AND DE FORMED BY THE LOADS CORRESPONDING TO TIME STEP NO 1 K2 N LOAD GEOMETRIC MATRIX FOR N CIRC WAVES CORRESPONDING TO THE TOTAL LOAD AT STEP NO 2 LAMBDA THE EIGENVALUE DONT CONCERN YOURSELF WITH THE ABSOLUTE VALUE OF THIS ONLY THE SIGN OF THE MINIMUM LAMBDA AND THE RELATIVE VALUES OF LAMBDA FOR VARIOUS N ARE SIGNIFICANT IF PLASTICITY OCCURS Q THE EIGENVECTOR BUCKLING MODE ITERATIONS HAVE CONVERGED FOR EIGENVAL
17. END TRIAL NO 1 ITERATION NO 1 MAXIMUM DISPLACEMENT DISPLACEMENT ENDUV 1 2799E 05 TRIAL NO 1 ITERATION NO 2 MAXIMUM DISPLACEMENT DISPLACEMENT ENDUV 1 2799E 05 1 30416356E 05 END NEWTON RAPHSON ITERATIONS HAVE CONVERGED NEXT CALCULATE THE PREBUCKLING STRAINS AND UPDATE THE MATERIAL PROPERTIES ENTER THE NEWTON RAPHSON ITERATION LOOP FOR TIME STEP NO 2 TIME 1 000000E 00 TRIAL NO 2 ITERATION NO 1 MAXIMUM DISPLACEMENT 1 30416356E 05 END DISPLACEMENT ENDUV 1 2799E 05 NEWTON RAPHSON ITERATIONS HAVE CONVERGED NEXT CALCULATE THE PREBUCKLING STRAINS AND UPDATE THE MATERIAL PROPERTIES ALL INFORMATION HAS BEEN STORED UP TO AND INCLUDING TIME STEP NO 2 CURRENT TIME 1 000E 00 Seg 1 Max eff strain 0 0000 00 material ok Strain margin 1 0000E 17 Seg 2 Max eff strain 0 0000 00 material ok Strain margin 1 0000E 17 Seg 3 Max eff strain 0 0000 00 material ok Strain margin 1 0000E 17 Maximum prebuckling displacement WPREMX 1 3042E 05 Displacement margin WPRMAR 7 6668E 03 Maximum Displacement time time step WPREMX TIME KSTEP 2 0 000000E 00 0 000000E 00 0 000000E 00 0 000000E 00 1 304164E 05 1 000000E 00 End Displacement time time step ENDUV TIME KSTEP 2 0 000000E 00 0 000000E 00 0 000000E 00 0 000000E 00 1 279876E 05 1 000000E 00 End of displacement time curve for KSTEP 2 TIME STEP NO 2 TIME 1 000E 00 N 6 CIRCUMFERENTIAL WAVES STABILITY DETERMINANT 1 948
18. ETUP session The files now existing in the working directory are as follows rw r r 1 bush bush 14760 Feb 19 10 23 1 ALL rw r r 1 bush bush 36588 Feb 19 10 46 1 BLK rw r r 1 bush bush 14749 Feb 19 10 29 1 DOC rw r r 1 bush bush 1213 Feb 19 10 43 1 IMP rw r r 1 bush bush 633 Feb 19 11 08 1 rw r r 1 bush bush 12320 Feb 19 10 46 1 MAI rw r r 1 bush bush 21787 Feb 19 10 46 1 0UT rw r r 1 bush bush 126464 Feb 19 10 46 1 RAN rw r r 1 bush bush 4209 Feb 19 09 41 1 SEG1 rw r r 1 bush bush 2948 Feb 19 09 47 1 SEG2 rw r r 1 bush bush 2948 Feb 19 09 54 1 SEG3 rw r r 1 bush bush 4680 Feb 19 10 14 1 SEG4 The new file 1 IPP contains the input data for POSTSETUP the 1 1 file IPRINT control 1 or 2 or 3 for list output IPLOT control 0 or 1 or 2 or 3 for plot output 5 NLAST plot options 1 0 2geometry 1 u v w Do you want to plot the discretized model Are there any regions for which you want expanded plots NMODES quantity of buckling modes to be listed plotted 5 5 5 n lt NTHMOD i ith mode calculated in last main run i 1 NWAVE i no of circ waves in the ith mode i 1 Do you want buckling modal output for all the segments OY OY bush gt bosorpost Enter case name 1 B background or F foreground f Running BOSOR5 bosorpost case 1 Executing bosorpost Normal termin
19. FOLLOWS Do you want to include smeared stiffeners LAYERS number of layers max 6 Are all the layers of constant thickness MATL type of material for shell wall layer no 1 T i thickness of ith layer i 1 leftmost T 1 G i shear modulus of ith layer G 1 EX i modulus in meridional direction EX 1 EY i modulus in circumferential direction EY 1 UXY i Poisson s ratio EY UXY EX UYX UXY 1 SM i mass density e g alum 00025 lb sec 2 in 4 SM 1 ALPHA1 i coef thermal exp in merid direction ALPHA1 1 ALPHA2 i coef thermal exp in circ direction ALPHA2 1 EPSALW i maximum allowable eff strain percent EPSALW 1 Do you wish to include plasticity in this segment Do you wish to include creep in this segment Is this a new shell wall material Do you want to have C i j printed for this segment END OF DATA FOR THIS SEGMENT GLOBAL DATA BEGINS LOADING TIME FUNCTIONS FOLLOW Do you want information on time functions for loading IUTIME control for time increment 0 or 1 IUTIME DTIME time increment TMAX maximum time to be encountered during this case NFTIME number of different functions of time NPOINT no of points j for ith load factor F i j i T i j jth time callout for ith time function j 1 T i j jth time callout for ith time function j 2 F i j jth value for ith load factor j 1 F i j jth value for ith load factor j 2 CONSTRAINT CONDI
20. February 19 2011 BOSOR5 RUN STREAM STARTING FROM SCRATCH Commands from the user are in 16 pt bold face Note the string bush gt is not part of the command typed by the user The purpose of this run stream is to generate the valid input file for BOSOR5 called 1 ALL The BOSOR5 sample case 1 ALL is analogous to the BIGBOSOR4 sample case also called 1 ALL Note however that the input data for BOSOR5 are somewhat different from the input data for BIGBOSOR4 The valid input file 1 ALL is generated mostly by use of the command INPUT by means of which an interactive session is launched in which the user generates a number of files 5 61 SEG2 in which denotes the user selected name for the case which in this case is 1 First go to a working directory where you want to run BOSOR5 Then do the following bush bosor5log BOSOR5 commands have been activated Below are the BOSOR5 commands listed in the order in which you would probably use them input interactive input of data for each segment assemble concatenates the segment data files bosorread runs BOSOR5 pre processor mainsetup interactive input of data for main processor bosormain runs BOSOR5 main processor postsetup interactive input of data for post processor bosorpost runs BOSOR5 post processor bosorplot generates plot files from most previous run Cleanup delete all case files except for DOC file getsegs generate
21. ME 1 00000000E 00 CURRENT TIME INCREMENT 1 00000000E 00 SEGMENT PRESSURE MULTIPLIER TEMPERATURE MULTIPLIER MULTIPLY THESE AMPLITUDES BY DISTRIBUTIONS GIVEN FOR EACH SEGMENT 1 1 00000000E 00 0 00000000E 00 2 0 00000000E 00 0 00000000E 00 3 0 00000000E 00 0 00000000E 00 0 TIME STEP NO 2 TIME 1 000E 00 N 10 CIRCUMFERENTIAL WAVES STABILITY DETERMINANT 2 646E 07 10 470 TIME STEP 2 NO OF NEGATIVE ROOTS 9 NO OF LAGRANGE MULTIPLIERS 9 STABILITY DETERMINANT DOES NOT CHANGE SIGN IN THE TIME INTERVAL UP TO AND INCLUDING TIME STEP NO 2 FOR THE RANGE OF CIRCUMFERENTIAL WAVE NUMBERS TESTED IN THIS RUN end of the 1 MAI file The following apply 1 The material response is entirely elastic in this case because the applied loading is very small 2 The output of especial significance in the above list is the following ITERATIONS HAVE CONVERGED FOR EIGENVALUE NO 1 EIGENVALUE 2 45506E 03 5 CIRCUMFERENTIAL WAVES ITERATIONS HAVE CONVERGED FOR EIGENVALUE NO 1 EIGENVALUE 2 14970E 03 6 CIRCUMFERENTIAL WAVES ITERATIONS HAVE EIGENVALUE ITERATIONS HAVE EIGENVALUE ITERATIONS HAVE EIGENVALUE ITERATIONS HAVE EIGENVALUE ITERATIONS HAVE EIGENVALUE ITERATIONS HAVE EIGENVALUE ITERATIONS HAVE EIGENVALUE ITERATIONS HAVE EIGENVALUE ITERATIONS HAVE EIGENVALUE ITERATIONS HAVE EIGENVALUE ITERATIONS HAVE EIGENVALUE ITERATIONS HAVE EIGENVALUE
22. PLACEMENT ENDUV 0 0000E 00 NEWTON RAPHSON ITERATIONS HAVE CONVERGED NEXT CALCULATE THE PREBUCKLING STRAINS AND UPDATE THE MATERIAL PROPERTIES ALL INFORMATION HAS BEEN STORED UP TO AND INCLUDING TIME STEP NO 1 CURRENT TIME 0 000E 00 Seg 1 Max eff strain 0 0000 00 material ok Strain margin 1 0000E 17 Seg 2 Max eff strain 0 0000E 00 material ok Strain margin 1 0000E 17 Seg 3 Max eff strain 0 0000E 00 material ok Strain margin 1 0000E 17 Maximum prebuckling displacement WPREMX 0 0000E 00 Displacement margin WPRMAR 1 0000E 17 Maximum Displacement time time step WPREMX TIME KSTEP 1 0 000000E 00 0 000000E 00 0 000000 00 0 000000E 00 End Displacement time time step ENDUV TIME KSTEP 1 0 000000E 00 0 000000E 00 0 000000E 00 0 000000E 00 End of displacement time curve for KSTEP 1 TIME STEP NO 1 TIME 0 000E 00 N 6 CIRCUMFERENTIAL WAVES STABILITY DETERMINANT 1 949E 06 10 470 TIME STEP 1 NO OF NEGATIVE ROOTS 9 NO OF LAGRANGE MULTIPLIERS 9 1 CALCULATIONS BEGIN FOR TIME STEP NUMBER 2 TIME 1 00000000E 00 CURRENT TIME INCREMENT 1 00000000E 00 SEGMENT PRESSURE MULTIPLIER TEMPERATURE MULTIPLIER MULTIPLY THESE AMPLITUDES BY DISTRIBUTIONS GIVEN FOR EACH SEGMENT 1 1 00000000E 00 0 00000000E 00 2 0 00000000E 00 0 00000000E 00 3 0 00000000E 00 0 00000000E 00 0 ENTER THE NEWTON RAPHSON ITERATION LOOP FOR TIME STEP NO 2 TIME 1 000000E 00 1 30416347E 05
23. STAT please include the endpoints of the shell segment BOSOR5 linearly interpolates the pressure and meridional traction between callout points that you will provide along the meridian See the illustration at the top of p P45 NPSTAT number of meridional callouts for pressure 2 2 Next provide meridional callout points for pressure NTYPE control for meaning of loading callout 2 z 3 r 2 2 Z I axial coordinate of Ith loading callout z 1 0 0 000000 Z I axial coordinate of Ith loading callout z 2 0 453 0 4530000 Next provide normal pressure and meridional traction at the meridional callouts PN J normal pressure at meridional callout pt no 1 h PN is positive as shown in the top figure on p P45 Pressure between callouts is calculated by BOSOR5 by linear interpolation The actual pressure is a product PN f time in which the function of time f time remains to be Specified PN J normal pressure at meridional callout pt no 1 1 1 000000 PN J normal pressure at meridional callout pt no 2 1 1 000000 PT J meridional traction at callout point no 1 0 0 PT J meridional traction at callout point no 2 0 0 ISTEP control integer for time variation of pressure h Note that the same time function is to be associated with both the normal pressure and the meridional traction The control integer ISTEP is a pointer which will cause the appropriate function of tim
24. TIONS FOLLOW How many segments are there in the structure H H H 0 H 1 1 1 0 0 0 0 0 Y H n H H H 0 H 0 H Y 1 1 1 6 1 1 1 1 0 0 Y H H H 0 H 0 H Y 1 4 2 10 1 1 1 1 0 0 Y H n 0 1000000 AU 4 47 HUY 47 47 47 HUY UU 47 47 X Y HY 47 uuu 4 47 4 4 47 X Y X UY X HUY HY HY HY HY HY HY X X Y Y CONSTRAINT CONDITIONS FOR SEGMENT NO 1 1 1 1 POLES INPUT FOLLOWS Number of poles places where r 0 in SEGMENT INPUT FOR CONSTRAINTS TO GROUND FOLLOWS At how many stations is this segment constrained to ground INODE nodal point number of constraint to ground INODE 1 IUSTAR axial displacement constraint 0 or 1 or 2 IVSTAR circumferential displacement 0 free l constrained IWSTAR radial displacement 0 free l constrained 2 imposed ICHI meridional rotation 0 free 1 constrained 2 imposed D1 radial component of offset of ground support D2 axial component of offset of ground support Is this constraint the same for both prebuckling and buckling JUNCTION CONDITION INPUT FOLLOWS Is this segment joined to any lower numbered segments CONSTRAINT CONDITIONS FOR SEGMENT NO 2 2 2 2 POLES INPUT FOLLOWS Number of poles places where r 0 in SEGMENT INPUT FOR CONSTRAINTS TO GROUND FOLLOWS At how many stations is this segment constrained to ground JUNCTION CONDITION INPUT FOLLOWS Is this
25. TUP interactive session We now have the following files pertaining to the case called 1 rw r r 1 bush bush 14760 Feb 19 10 23 1 ALL rw r r 1 bush bush 36588 Feb 19 10 29 1 BLK rw r r 1 bush bush 14749 Feb 19 10 29 1 DOC rw r r 1 bush bush 1213 Feb 19 10 43 1 IMP rw r r 1 bush bush 9467 Feb 19 10 29 1 0UT rw r r 1 bush bush 102912 Feb 19 10 29 1 RAN rw r r 1 bush bush 4209 Feb 19 09 41 1 SEG1 rw r r 1 bush bush 2948 Feb 19 09 47 1 SEG2 rw r r 1 bush bush 2948 Feb 19 09 54 1 SEG3 rw r r 1 bush bush 4680 Feb 19 10 14 1 SEG4 The interactive MAINSETUP input data are saved in the file 1 a list of which follows 1 IMP file 2 INDIC analysis type indicator 0 or 2 or 3 INDIC n Type HELP or H for more information on INDIC N for no more 0 IDEFORM indicator 0 or 1 for type of plasticity theory 1 ICPRE control 0 or 1 for type of eigenvalue problem n Do you want to reverse the rate of loading 0 KSTEP starting time step number 2 KMAX maximum less than 49 time step number 5 MAXTRL maximum number of trials at each load level 6 ITMAX maximum number of Newton iterations for each trial 0 ITIME control 0 or 1 for time increments n Do you wish to force the material to remain elastic 6 NOB starting number of circ waves buckling analysis 5 NMINB minimum number of circ waves buckling analy
26. UE NO 1 EIGENVALUE 2 45506E 03 5 CIRCUMFERENTIAL WAVES ITERATIONS HAVE CONVERGED FOR EIGENVALUE NO 1 EIGENVALUE 2 14970E 03 6 CIRCUMFERENTIAL WAVES ITERATIONS HAVE CONVERGED FOR EIGENVALUE NO 1 EIGENVALUE 1 93669E 03 7 CIRCUMFERENTIAL WAVES ITERATIONS HAVE CONVERGED FOR EIGENVALUE NO 1 EIGENVALUE 1 79806E 03 8 CIRCUMFERENTIAL WAVES ITERATIONS HAVE CONVERGED FOR EIGENVALUE NO 1 EIGENVALUE 1 71769E 03 9 CIRCUMFERENTIAL WAVES ITERATIONS HAVE CONVERGED FOR EIGENVALUE NO 1 EIGENVALUE 1 68283E 03 10 CIRCUMFERENTIAL WAVES ITERATIONS HAVE CONVERGED FOR EIGENVALUE NO 1 EIGENVALUE 1 68370E 03 11 CIRCUMFERENTIAL WAVES ITERATIONS HAVE CONVERGED FOR EIGENVALUE NO 1 EIGENVALUE 1 71289E 03 12 CIRCUMFERENTIAL WAVES ITERATIONS HAVE CONVERGED FOR EIGENVALUE NO 1 EIGENVALUE 1 76469E 03 13 CIRCUMFERENTIAL WAVES ITERATIONS HAVE EIGENVALUE ITERATIONS HAVE EIGENVALUE ITERATIONS HAVE EIGENVALUE ITERATIONS HAVE EIGENVALUE ITERATIONS HAVE EIGENVALUE ITERATIONS HAVE EIGENVALUE ITERATIONS HAVE EIGENVALUE CONVERGED FOR EIGENVALUE NO 1 1 83455E 03 14 CIRCUMFERENTIAL CONVERGED FOR EIGENVALUE NO 1 1 91879E 03 15 CIRCUMFERENTIAL CONVERGED FOR EIGENVALUE NO 1 2 01424E 03 16 CIRCUMFERENTIAL CONVERGED FOR EIGENVALUE NO 1 2 11815E 03 17 CIRCUMFERENTIAL CONVERGED FOR EIGENVALUE NO 1 2 22801E 03 18 CIRCUMFERENTIAL CONVERGED FOR EIGENVALUE NO 1 2 34147E 03 19 CIRCUMFERENTI
27. ain coordinates of s s curve EPS 1 0 0 000000 EPS i strain coordinates of s s curve EPS 2 1 1 000000 SIG i stress coordinates of s s curve SIG 1 0 0 000000 SIG i stress coordinates of s s curve SIG 2 10 8E 06 0 1080000E 08 Do you want to have C i j printed for this segment n n Want to add more structural segments y Which segment is this 2 Are you Beading adding to or checking an existing file n NE of node points 5 min 98 max 10 control integer 1 or 2 or 3 for nodal point spacing 3 Geometry of the current segment NSHAPE indicator 1 2 or 4 for geometry of meridian 1 1 R1 radius at beginning of segment see p P7 5 218 5 218000 21 axial coordinate at beginning of segment 0 2265 0 2265000 R2 radius at end of segment 4 882 4 882000 72 axial coordinate at end of segment 0 2265 0 2265000 Imperfection geometry IMP indicator for imperfection 0 none 1 some 0 0 NTYPEZ control 1 or 3 for reference surface location 3 3 ZVAL distance from leftmost surf to reference surf 0 0075 0 7500000E 02 Do you want to print out r s r s etc for this segment n n NRINGS number max 20 of discrete rings in this segment 0 K elastic foundation modulus e g lb in 3 in this seg 0 0 Do you want general information on loading n n Temperature rise above or fall below that corresponding to the zero stress state You will be asked to provide distributio
28. ation bosorpost Case 1 postprocessor run completed Next choose from the commands BOSORPLOT MAINSETUP POSTSETUP INPUT CLEANUP GETSEGS OR MODIFY 0 056u 0 076s 0 00 28 42 8 0 0k 04010 1lpf 0w The files now existing in the working directory are as follows rw r r 1 bush bush 14760 Feb 19 10 23 1 ALL rw r r 1 bush bush 36588 Feb 19 10 46 1 BLK rw r r 1 bush bush 14749 Feb 19 10 29 1 DOC rw r r 1 bush bush 1213 Feb 19 10 43 1 IMP rw r r 1 bush bush 633 Feb 19 11 08 1 IPP rw r r 1 bush bush 45 Feb 19 11 10 1 LAB rw r r 1 bush bush 12320 Feb 19 10 46 1 MAI rw r r 1 bush bush 26833 Feb 19 11 10 1 0UT rw r r 1 bush bush 2902 Feb 19 11 10 1 PLT2 rw r r 1 bush bush 5046 Feb 19 11 10 1 POS rw r r 1 bush bush 126976 Feb 19 11 10 1 RAN rw r r 1 bush bush 4209 Feb 19 09 41 1 SEG1 rw r r 1 bush bush 2948 Feb 19 09 47 1 SEG2 rw r r 1 bush bush 2948 Feb 19 09 54 1 SEG3 rw r r 1 bush bush 4680 Feb 19 10 14 1 SEG4 The output from the BOSOR5 post processor BOSORPOST is contained in the 1 POS file which will not be listed here Next get a plot of the buckling mode chosen during the POSTSETUP interactive session bush bosorplot Please enter the BOSOR5 case name 1 Do you want to use Xgraph or create a PostScript file Choose X or P p One moment please Text file s have been created containing plot data The names of the files explain to a greater or lesser extent what the
29. constrained 2 imposed 0 ROM rotation 0 free 1 2 imposed 0 D1 vamus component of offset of ground support 0 D2 OR component of offset of ground support 0 Is this ae the same for both prebuckling and buckling y Y Is this segment joined to any lower numbered segments n n CONSTRAINT CONDITIONS FOR SEGMENT NO ISEG 2 Number of poles places where r 0 in SEGMENT 0 0 At how many stations is this segment constrained to ground 0 0 Is this segment joined to any lower numbered segments y y At how may stations is this segment joined to previous segs 1 1 INODE node in current segment ISEG of junction INODE 1 1 JSEG AM no of lowest segment involved in junction 1 JNODE in lowest segment JSEG of junction 6 IUSTAR displacement 0 not slaved 1 51 1 IVSTAR Ser OEIL displacement 0 not slaved 1 slaved 1 IWSTAR displacement 0 not slaved 1 51 1 ICHI rotation 0 not slaved 1 51 1 D1 rarus component of juncture gap 0 D2 axial component of juncture gap 0 Is this constraint the same for both prebuckling and buckling y Y CONSTRAINT CONDITIONS FOR SEGMENT NO ISEG 3 Number of poles places where r 0 in SEGMENT 0 0 At how many stations is this segment constrained to ground 0 Is this joined to any lower numbered segments y At how may stations is this segment joined to previous segs 1 INODE Sod in
30. crete rings in this segment 0 0 K elastic foundation modulus e g lb in 3 in this seg 0 0 Do you want general information on loading n n Temperature rise above or fall below that corresponding to the zero stress state You will be asked to provide distributions along the meridian and through the thickness See pp P32 P39 NTSTAT number of temperature callout points along meridian 0 0 Next provide input for normal pressure and meridional traction NPSTAT number of meridional callouts for pressure 0 0 Next please provide applied line loads and or imposed axisymmetric displacement components for this shell segment LINTYP control for line loads or disp 0 none l1 some 0 0 Input for orthotropic layered wall construction follows Note circumferential or meridional stiffeners can be included by smearing their properties as shown on p P55 and as described below Do you want to include smeared stiffeners n n LAYERS number of layers max 6 1 1 Are all the layers of constant thickness y y MATL type of material for shell wall layer no 1 1 1 T i thickness of ith layer i 1 leftmost T 1 0 015 0 1500000E 01 G i shear modulus of ith layer G 1 4 051013E 06 4051013 EX i modulus in meridional direction EX 1 10 8E 06 0 1080000E 08 EY i modulus in circumferential direction EY 1 10 8E 06 0 1080000E 08 UXY i Poisson s ratio EY UXY EX UYX UXY 1 333 0 333000
31. cture gap Is this constraint the same for both prebuckling and buckling RIGID BODY CONSTRAINT INPUT FOLLOWS Given existing constraints are rigid body modes possible WPRALL maximum allowable displacement WPRALL end of 1 ALL file Next execute BOSORREAD bush bosorread Enter case name 1 B background or F foreground f Running BOSOR5 bosorread case 1 Executing bosorread Normal termination bosorread Case 1 preprocessor run completed Next give the command mainsetup 0 191u 0 087s 0 00 60 45 0 0 0k 04010 2pf 0w bush gt mainsetup Please enter case name 1 Are you correcting adding to or checking an existing file n n INDIC analysis type indicator 0 or 2 or 3 INDIC h 0 nonlinear axisymmetric stress and collapse analysis 2 axisymmetric prebuckling states and stability determinant are calculated for several load time steps See p M3 3 stability determinant is calculated for a case in which prebuckling states have been obtained in a previous run See p M5 INDIC analysis type indicator 0 or 2 or 3 INDIC 2 2 Type HELP or H for more information on INDIC N for no more h INDIC 0 means that nonlinear axisymmetric stress analysis will be performed for a sequence of time load steps specified by you either in the BOSOR5 preprocessor or in the following The results for every time step are saved so that the case can be restarted at any ti
32. current segment ISEG of junction INODE 1 4 JSEG He no of lowest segment involved in junction 2 JNODE ee in lowest segment JSEG of junction 10 eee displacement 0 not slaved 1 51 1 IVSTAR displacement 0 not slaved 1 51 1 IWSTAR E displacement 0 not slaved 1 51 1 ICHI iail rotation 0 not slaved 1 slaved 1 D1 UN component of juncture gap 0 D2 axial component of juncture gap 0 Is this constraint the same for both prebuckling and buckling y Y It may be necessary to provide additional constraint to ground in order to prevent rigid body motion in the bifurcation buckling phase of the analysis All possible types of rigid body motion are shown on p P73 Rigid body motion corresponds to n 0 or n 1 circumferential waves There is no rigid body component for any harmonic with n greater than or equal to 2 Note that the following question applies only to the bifurcation buckling phase of the analysis not to the axisymmetric prebuckling phase Given existing constraints are rigid body modes possible n n WPRALL maximum allowable displacement WPRALL h There is no more help Do your best WPRALL maximum allowable displacement WPRALL 0 1 0 1000000 If you have completed input for all structural segments and for the constraint conditions next give the command ASSEMBLE END OF INTERACTIVE INPUT SESSION There now exist in the
33. data represent Some plot files contain data for more than one plot 1 1 R Z EIGENMODE 1 N 10 CR to QUIT Please choose the number of the file you wish to plot 1 Plotting Undeformed amp Deformed Axial Station as a function of Radius The PostScript file metafile ps has been created Please choose one of the three options below 1 Rename the PostScript file this is useful if you don t have access to a PostScript printer on your machine but you wish to save to a file so you can later transfer it to a different machine for printing Example mv metafile ps plotl ps 2 Enter an lpr command This is useful if your default printer is not PostScript but there is a PostScript printer available on your system Example lpr PApplelaser metafile ps 3 Press the return key This executes the command lpr metafile ps This assumes that your default printer is a PostScript printer Enter your command enter Printing PostScript plot on the default printer Text file s have been created containing plot data The names of the files explain to a greater or lesser extent what the data represent Some plot files contain data for more than one plot 1 1 R Z EIGENMODE 1 N 10 CR to QUIT Please choose the number of the file you wish to plot lt enter gt The files now existing in the working directory are as follows rw r r 1 bush bush 14760 Feb 19 10 23 1 ALL rw r r 1 bush bush 36588 Feb 19 10 46 1 BLK rw
34. de the time variations of loading which correspond to the pointers IDTEMP ISTEP etc that you have already given Each time varying load factor is to be provided by you in the form of a vector of time callouts T i j j 1 NPOINT followed by a vector of corresponding load factors F i j j 1 NPOINT where i 1 2 3 NFTIME The index j is in the inner loop NPOINT no of points j for ith load factor F i j i 1 h NPOINT must be greater than or equal to 2 and less than or equal to 50 For constant or linearly varying loads NPOINT should be 2 See p P63 for an example In common cases the time increase is identified directly with the load increase time load essentially In such a case NPOINT 2 NPOINT no of points j for ith load factor F i j 1 2 2 T i j jth time callout for ith time function j 1 h T i j must be less than or equal to TMAX T i j jth time callout for ith time function j 1 0 0 000000 T i j jth time callout for ith time function j 2 10000 10000 00 Next provide the vector of load factors F i j i F i j jth value for ith load factor j 1 h For common cases no creep it is advisable to identify the load factor F i j with time T i j Thus F i j T i j in other words f time time Then in the output when time is printed you will know directly what the load is F i j jth value for ith load factor j 1 0 0 000000 F i j jth value for ith load
35. e to be associated with the spatial pressure distribution that you have just provided Different functions of time can be associated with the pressure distributions in different shell segments The exact nature of these time functions will be asked of you later Right now all you need do is to specify 1 or 2 or 3 or other Simple integer Start with an appropriate value which depends on what other loads you have already specified in this case up to now ISTEP should be unity if this is the first load ever specified in this case Each time a new time function is to be introduced use a higher integer higher by 1 than has ever been used before to specify the time variation of any load whether it be for a previously specified temperature distribution pressure or surface traction distribution or line load This word previous includes loads that you have specified in previous segments as well as those specified previously in the current segment ISTEP control integer for time variation of pressure 1 1 Do you want to print out distributed loads along meridian n n LINTYP control for line loads or disp 0 none 1 some h Line loads must always be associated with a discrete ring and they are assumed to act at the discrete ring centroid as shown in the Fig at the bottom of p P47 Note that hydrostatic pressure gives rise to line loads pr 2 at the ends of the shell structure thus requiring you to use LINTYP 1 for those segments i
36. escribed above Type H for more information on INDIC N for no more Type HELP or H for more information on INDIC N for no more h Note In problems involving bifurcation buckling in the plastic range of material behavior the actual values of the eigenvalues obtained by BOSOR5 are not too meaningful The sign of the eigenvalues and their relationship to eachother that is for which circumferential wave number is there a minimum eigenvalue are important however Briefly the eigenvalue analysis in BOSOR5 has two purposes 1 to help the search for a minimum buckling load with respect to the number of circumferential waves 2 to yield buckling mode shapes which guide the engineer toward a better design Type HELP or H for more information on INDIC N for no more h There is no more help Do your best Type HELP or H for more information on INDIC N for no more n n IDEFORM indicator 0 or 1 for type of plasticity theory h IDEFORM 0 means that flow theory will be used to calculate the constitutive law for both the prebuckling and the bifurcation buckling analyses IDEFORM 1 means that flow theory will be used in the prebuckling analysis and deformation theory in the bifurcation buckling analysis NOTE In order to run INDIC 3 with deformation theory you must have previously run INDIC 2 with IDEFORM 1 IDEFORM indicator 0 or 1 for type of plasticity theory 0 0 ICPRE control 0 or 1 for type o
37. f eigenvalue problem h In cases for which all loads and temperatures vary with pseudo time in the same proportion use ICPRE 1 Otherwise use ICPRE 0 For more details see the discussion on the right hand side of p 407 of the paper by Lagae and Bushnell Elastic plastic buckling of torispherical vessel heads Nuclear Engineering and Design Vol 48 1978 pp 405 414 ICPRE control 0 or 1 for type of eigenvalue problem 1 1 Do you want to reverse the rate of loading h For example you may wish to unload from the latest converged step or from some earlier step Do you want to reverse the rate of loading n n KSTEP starting time step number h If this is the first run not a restart KSTEP must be O0 If this is a restart then KSTEP must be equal to a value for which prebuckling results have already been obtained in a previous run After the first run KSTEP 1 corresponds to the first time step KSTEP starting time step number 0 0 KMAX maximum less than 49 time step number h As a rule of thumb do less than 10 time steps per run Look at your results after each run and make use of the restart capability KMAX maximum less than 49 time step number 2 2 MAXTRL maximum number of trials at each load level h The figure on p M7 explains what is meant by a trial In BOSOR5 several trials for a converged solution are attempted at each time step level of loading The purpose of each trial is to obtain
38. ion modulus e g lb in 3 in this seg TEMPERATURE INPUT FOLLOWS Do you want general information on loading NTSTAT number of temperature callout points along meridian PRESSURE INPUT FOLLOWS NPSTAT number of meridional callouts for pressure LINE LOAD INPUT FOLLOWS LINTYP control for line loads or disp 0 2none l some SHELL WALL CONSTRUCTION FOLLOWS Do you want to include smeared stiffeners LAYERS number of layers max 6 Are all the layers of constant thickness MATL type of material for shell wall layer no 1 T i thickness of ith layer i 1 leftmost T 1 G i shear modulus of ith layer G 1 EX i modulus in meridional direction EX 1 EY i modulus in circumferential direction EY 1 UXY i Poisson s ratio EY UXY EX UYX UXY 1 SM i mass density e g alum 00025 lb sec 2 in 4 SM 1 ALPHA1 i coef thermal exp in merid direction ALPHA1 1 ALPHA2 i coef thermal exp in circ direction ALPHA2 1 EPSALW i maximum allowable eff strain percent EPSALW 1 Do you wish to include plasticity in this segment Do you wish to include creep in this segment Is this a new shell wall material Do you want to have C i j printed for this segment END OF DATA FOR THIS SEGMENT SEGMENT NUMBER 3 3 3 3 3 3 3 3 NODAL POINT DISTRIBUTION FOLLOWS 7 3 H 1 4 882000 0 1820000 4 882000 0 2710000 H 0 H 3 0 1500000 01 0 0 0 0 0 n 1 Y
39. ions not the temporal variations f t themselves The f t to which the pointers point will be asked for after data for all the shell segments have been provided by you See pp P30 P31 for discussion and illustrations There are three types of loading 1 temperature 2 normal pressure and meridional traction and 3 line loads and or imposed displacement components applied at centroids of discrete rings Temperature rise above or fall below that corresponding to the zero stress state You will be asked to provide distributions along the meridian and through the thickness See pp P32 P39 NTSTAT number of temperature callout points along meridian h NTSTAT 0 means no temperature distrib to be specified NTSTAT 1 means temperature is uniform along meridian NTSTAT 1 means temperature is nonuniform along meridian If NTSTAT 1 you will be asked to provide callout points See illustrations on p P33 and p P35 BOSOR5 will automatically linearly interpolate between callout points Make sure to include end points of the shell segment in determining NTSTAT NTSTAT number of temperature callout points along meridian 0 0 Next provide input for normal pressure and meridional traction NPSTAT number of meridional callouts for pressure h NPSTAT 0 means no pressure or meridional traction NPSTAT 1 means uniform distributed loading NPSTAT 1 means meridionally nonuniform loading In determining NP
40. me step It is also possible to restart with a different value of INDIC INDIC 2 means that a nonlinear axisymmetric stress analysis will be performed and that the stability determinant will be calculated for several time steps for a certain fixed number NOB of circumferential waves If the stability determinant for NOB waves changes sign in the user specified time range then bifurcation buckling loads are calculated for a range of circumferential wave numbers NMINB through NMAXB in increments of INCRB with NMINB NMAXB INCRB to be provided by you See the figure at the bottom of p M3 Type H for more help N for no more Type HELP or H for more information on INDIC N for no more h INDIC 2 continued If the stability determinant does not change sign eigenvalues for the range NMINB to NMAXB are still computed In either case whether or not the stability determinant changes sign you should pursue the buckling analysis in a restart for a new circumferential wavenumber that wavenumber corresponding to the minimum eigenvalue as shown in Fig 3 at the bottom of p M3 INDIC 3 means that the stability determinant for a given number NOB of circumferential waves will be calculated for a sequence of time steps for which the prebuckling analysis was done in a previous run with INDIC 0 or INDIC 2 Bifurcation buckling loads are calculated for a user provided range NMINB to NMAXB of circumferential wavenumbers as d
41. n which pr 2 acts Imposed axisymmetric displacement components USTAR WSTAR CHI see page P66 left hand top for positive values must always be associated with a discrete ring In the following input for loading V K can mean axial load or axial displacement note positive V load p P47 is in opposite direction from positive V displacement USTAR on p P66 HF K can mean radial load or radial displacement FM K can mean meridional moment or meridional rotation LINTYP control for line loads or disp 0 none l1 some 0 0 Input for orthotropic layered wall construction follows Note circumferential or meridional stiffeners can be included by smearing their properties as shown on p P55 and as described below Do you want to include smeared stiffeners h There is no more help Do your best Do you want to include smeared stiffeners n n LAYERS number of layers max 6 h Be sure to include in LAYERS any layers corresponding to smeared stringers and or smeared rings Layers are numbered from left to right as shown in the figure on the bottom of p P51 left and right are based on the assumption that you are facing in the direction of increasing meridional arc length s LAYERS number of layers max 6 1 1 Are all the layers of constant thickness h There is no more help Do your best Are all the layers of constant thickness y Y MATL type of material for shell wall layer no 1 h Layers are n
42. ns along the meridian and through the thickness See pp P32 P39 NTSTAT number of temperature callout points along meridian 0 0 Next provide input for normal pressure and meridional traction NPSTAT number of meridional callouts for pressure 0 0 Next please provide applied line loads and or imposed axisymmetric displacement components for this shell segment LINTYP control for line loads or disp 0 none l1 some 0 0 Input for orthotropic layered wall construction follows Note circumferential or meridional stiffeners can be included by smearing their properties as shown on p P55 and as described below Do you want to include smeared stiffeners n n LAYERS number of layers max 6 1 1 Are all the layers of constant thickness y y MATL type of material for shell wall layer no 1 1 1 T i thickness of ith layer i 1 leftmost T 1 0 015 0 1500000E 01 G i shear modulus of ith layer G 1 4 051013E 06 4051013 EX i modulus in meridional direction EX 1 10 8E 06 0 1080000E 08 EY i modulus in circumferential direction EY 1 10 8E 06 0 1080000E 08 UXY i Poisson s ratio EY UXY EX UYX UXY 1 333 0 3330000 SM i mass density e g alum 00025 lb sec 2 in 4 SM 1 00025 0 2500000E 03 ALPHA1 i coef thermal exp in merid direction ALPHA1 1 0 0 ALPHA2 i coef thermal exp in circ direction ALPHA2 1 0 0 EPSALW i maximum allowable eff strain percent EPSALW 1 1 6
43. o force the material to remain elastic n NOB starting number of circ waves buckling analysis 6 NMINB minimum number of circ waves buckling analysis 5 NMAXB maximum number of circ waves buckling analysis 20 INCRB increment in number of circ waves buckling 1 INITIAL BUCKLING OR VIBRATION WAVE NO 6 MINIMUM WAVE NO 5 MAXIMUM WAVE NO 20 INCREMENT 1 1 EIGENVALUES SOUGHT FOR EACH CIRCUMFERENTIAL WAVE NUMBER TIME starting time need not be zero in initial run 0 Do you want stations where plastic flow occurs listed y 1 CALCULATIONS BEGIN FOR TIME STEP NUMBER 1 TIME 0 00000000E 00 CURRENT TIME INCREMENT 1 00000000E 00 SEGMENT PRESSURE MULTIPLIER TEMPERATURE MULTIPLIER MULTIPLY THESE AMPLITUDES BY DISTRIBUTIONS GIVEN FOR EACH SEGMENT 1 0 00000000E 00 0 00000000E 00 2 0 00000000E 00 0 00000000E 00 3 0 00000000E 00 0 00000000E 00 ENTER THE NEWTON RAPHSON ITERATION LOOP FOR TIME STEP NO 1 TIME 0 000000E 00 TRIAL NO 1 ITERATION NO 1 MAXIMUM DISPLACEMENT DISPLACEMENT ENDUV 0 0000E 00 TRIAL NO 1 ITERATION NO 2 MAXIMUM DISPLACEMENT DISPLACEMENT ENDUV 0 0000E 00 0 00000000 00 END 0 00000000 00 END NEWTON RAPHSON ITERATIONS HAVE CONVERGED NEXT CALCULATE THE PREBUCKLING STRAINS AND UPDATE THE MATERIAL PROPERTIES ENTER THE NEWTON RAPHSON ITERATION LOOP FOR TIME STEP NO 1 TIME 0 000000E 00 TRIAL NO 2 ITERATION NO 1 MAXIMUM DISPLACEMENT 0 00000000E 00 END DIS
44. of this segment or in the shell wall of a previous shell segment Note that you must provide a stress strain curve here even if the same material has been specified previously for a discrete ring segment Is this a new shell wall material h There is no more help Do your best Is this a new shell wall material y Y Stress strain curve for material in shell wall layer no 1 NPOINT number of points in s s curve layer no 1 h Please include the stress strain coordinate 0 0 in your determination of a value for NPOINT NPOINT must be greater than or equal to 2 and less than 20 If the material is elastic rather than elastic plastic use NPOINT 2 use 0 and 1 for the strain coordinates and use 0 and E Young s modulus for the stress coordinates See p P55 for examples NPOINT number of points in s s curve layer no 1 2 2 NITEG no integration pts thru thickness layer no 1 h Use 3 or 5 or 7 or 9 5 is usually sufficient unless you are simulating residual stress patterns due to cold bending 3 is good for flanges of stringers or rings that are modelled as a shell wall layer smeared out NITEG no integration pts thru thickness layer no 1 h There is no more help Do your best NITEG no integration pts thru thickness layer no 1 5 5 Do you want to use power law for stress strain curve h There is no more help Do your best Do you want to use power law for stress strain curve n n EPS i str
45. ovided by you for each shell segment See p Pl for a list of the types of input data required NOTE Up to 200 segments are now permitted in BOSOR5 NMESH no of node points 5 min 98 max 11 11 NTYPEH control integer 1 or 2 or 3 for nodal point spacing 3 3 Geometry of the current segment NSHAPE indicator 1 2 or 4 for geometry of meridian 1 1 R1 radius at beginning of segment see p P7 5 218 5 218000 Z1 axial coordinate at beginning of segment 0 0 000000 R2 radius at end of segment 5 218 5 218000 Z2 axial coordinate at end of segment 0 453 0 4530000 Imperfection geometry IMP indicator for imperfection 0 none 1 some 0 0 NTYPEZ control 1 or 3 for reference surface location 3 3 ZVAL distance from leftmost surf to reference surf 0 0 Do you want to print out r s r s etc for this segment n n NRINGS number max 20 of discrete rings in this segment 0 0 K elastic foundation modulus e g lb in 3 in this seg 0 0 Do you want general information on loading y y The following input is related to loading of this segment All loads are considered to be axisymmetric and to be products of spatial times temporal functions For example the pressure p s time is given by p s time Po s f time in which s is the meridional arc length In this section you will be asked to provide only the spatial variation of the loads e g Po s and pointers to the temporal variat
46. r r 1 bush bush 14749 Feb 19 10 29 1 DOC rw r r 1 bush bush 1213 Feb 19 10 43 1 rw r r 1 bush bush 633 Feb 19 11 08 1 IPP rw r r 1 bush bush 45 Feb 19 11 10 1 LAB rw r r 1 bush bush 12320 Feb 19 10 46 1 MAI rw r r 1 bush bush 26833 Feb 19 11 10 1 0UT rw r r 1 bush bush 2902 Feb 19 11 10 1 PLT2 rw r r 1 bush bush 5046 Feb 19 11 10 1 POS rw r r 1 bush bush 126976 Feb 19 11 10 1 RAN rw r r 1 bush bush 4209 Feb 19 09 41 1 SEG1 rw r r 1 bush bush 2948 Feb 19 09 47 1 SEG2 rw r r 1 bush bush 2948 Feb 19 09 54 1 SEG3 rw r r 1 bush bush 4680 Feb 19 10 14 1 SEG4 rw r r 1 bush bush 13908 Feb 19 11 16 metafile ps The plot is contained in the Postscript file metafile ps cp metafile ps 1 10 gv 1 10 The plot plot nl0 ps is shown below ese peni eon 1 RZ EIGENMODE 1 N 10 Axial Station x 1073 7 ndeformed 150 0000 Deformed i LI i 100 0000 E 350 0000 i 300 0000 n 8 n o 250 0000 o i i B i o o V LI j 8 00 0000 i 150 0000 i 100 0000 i 50 0000 x 0 0000 24 4 ann 4 an 5 5 nsn 5 ihn s 18fifl 5 nn li plot nl0 ps 1 buckle nl0 png buckling mode eigenvector for N 10 circumferential waves The eigenvalue buckling load factor as listed above is EIGENVALUE 1 68283E 03 10 CIRCUMFERENTIAL WAVES cleanup
47. rmal pressure at meridional callout pt no 2 PT J meridional traction at callout point no 1 PT J meridional traction at callout point no 2 ISTEP control integer for time variation of pressure Do you want to print out distributed loads along meridian LINE LOAD INPUT FOLLOWS LINTYP control for line loads or disp 0 none 1 some SHELL WALL CONSTRUCTION FOLLOWS Do you want to include smeared stiffeners LAYERS number of layers max 6 Are all the layers of constant thickness MATL type of material for shell wall layer no 1 T i thickness of ith layer i 1 leftmost T 1 G i shear modulus of ith layer G 1 EX i modulus in meridional direction EX 1 EY i modulus in circumferential direction EY 1 UXY i Poisson s ratio EY UXY EX UYX UXY 1 SM i mass density e g alum 00025 lb sec 2 in 4 SM 1 ALPHA1 i coef thermal exp in merid direction ALPHA1 1 ALPHA2 i coef thermal exp in circ direction ALPHA2 1 EPSALW i maximum allowable eff strain percent EPSALW 1 Do you wish to include plasticity in this segment Do you wish to include creep in this segment Is this a new shell wall material 2 5 n 0 000000 1 000000 0 000000 0 1080000E 08 10 3 1 5 218000 0 2265000 4 882000 0 2265000 H 0 H 3 0 7500000E 02 n H oo n 1 1 0 1500000 01 4051013 0 1080000 08 0 1080000 08 0 3330000 0 2500000 03 0 0 1 6000
48. segment files from DOC file modify interactively modify a segment or global data file Please consult the following sources for more information about BOSOR5 1 bosor5 doc bosor5st ory good idea to print this file 2 Documents listed under HELP5 OVERVIEW DOC bush input Please enter case name 1 Do you want to provide data for a new structural segment or to add data to that for an existing structural segment Please answer Y or N y Which segment is this 1 1 Are you correcting adding to or checking an existing file n n BOSOR5 INPUT DATA INTERACTIVE MODE Initial prompts are short and contain data names a new user will not be familiar with Please type HELP or H instead of any datum called for and you will get more information on that datum Page numbers contained in some of the prompts refer to the original BOSOR5 user s manual BOSOR5 a computer program for buckling of elastic plastic complex shells of revolution including large deflections and creep Lockheed Missiles amp Space Co Report LMSC D407166 December 1974 Vol 1 User s manual input data This user s manual contains additional discussion and figures NOTE This version of BOSOR5 will handle up to 200 shell segments rather than the 25 stated as a limit in the user s manual Please provide a title 42 characters or less ALUMINUM FRAME BUCKLING NSEG number of shell segments less than 95 3 3 The following input must be pr
49. segment joined to any lower numbered segments At how may stations is this segment joined to previous segs INODE node in current segment ISEG of junction INODE 1 JSEG segment no of lowest segment involved in junction JNODE node in lowest segment JSEG of junction IUSTAR axial displacement 0 not slaved 1 slaved IVSTAR circumferential displacement 0 not slaved 1 slaved IWSTAR radial displacement 0 2not slaved 1 slaved ICHI meridional rotation 0 not slaved 1 slaved radial component of juncture gap axial component of juncture gap Is this constraint the same for both prebuckling and buckling CONSTRAINT CONDITIONS FOR SEGMENT NO 3 3 3 3 POLES INPUT FOLLOWS Number of poles places where r 0 in SEGMENT INPUT FOR CONSTRAINTS TO GROUND FOLLOWS At how many stations is this segment constrained to ground JUNCTION CONDITION INPUT FOLLOWS Is this segment joined to any lower numbered segments At how may stations is this segment joined to previous segs INODE node in current segment ISEG of junction INODE 1 JSEG segment no of lowest segment involved in junction JNODE node in lowest segment JSEG of junction IUSTAR axial displacement 0 not slaved 1 slaved IVSTAR circumferential displacement 0 not slaved 1 slaved IWSTAR radial displacement 0 not slaved 1 slaved ICHI meridional rotation 0 not slaved 1 slaved D1 radial component of juncture gap D2 axial component of jun
50. sis 20 NMAXB maximum number of circ waves buckling analysis 1 INCRB increment in number of circ waves buckling 0 TIME starting time need not be zero in initial run y Do you want stations where plastic flow occurs listed end of 1 IMP file bush bosormain Enter case name 1 B background or F foreground f Running BOSOR5 bosormain case 1 Executing bosormain Normal termination bosormain Case 1 mainprocessor run completed Next give the command mainsetup or postsetup 0 110u 0 077s 0 00 54 33 3 0 0k 04010 2pf 0w The files in the working directory are now as follows rw r r 1 bush bush 14760 Feb 19 10 23 1 ALL rw r r 1 bush bush 36588 Feb 19 10 46 1 BLK rw r r 1 bush bush 14749 Feb 19 10 29 1 DOC rw r r 1 bush bush 1213 Feb 19 10 43 1 IMP rw r r 1 bush bush 12320 Feb 19 10 46 1 MAI rw r r 1 bush bush 21787 Feb 19 10 46 1 0UT rw r r 1 bush bush 126464 Feb 19 10 46 1 RAN rw r r 1 bush bush 4209 Feb 19 09 41 1 SEG1 rw r r 1 bush bush 2948 Feb 19 09 47 1 SEG2 rw r r 1 bush bush 2948 Feb 19 09 54 1 SEG3 rw r r 1 bush bush 4680 Feb 19 10 14 1 SEG4 The file 1 MAI contains the output data from the execution of the BOSOR5 processor BOSORMAIN The 1 MAI file is as follows 1 MAI file output from BOSORMAIN 2 INDIC analysis type indicator 0 or 2 or 3 INDIC n Type HELP or H for
51. umbered from left to right as shown in the figure on the bottom of p P51 left and right are based on the assumption that you are facing in the direction of increasing meridional arc length s Layers corresponding to parts of smeared stiffeners must each be associated with a new material index number MATL type of material for shell wall layer no 1 1 1 T i thickness of ith layer i 1 leftmost T 1 0 182 0 1820000 G i shear modulus of ith layer G 1 4 051013E 06 4051013 EX i modulus in meridional direction EX 1 10 8E 06 0 1080000E 08 EY i modulus in circumferential direction EY 1 10 8 06 0 1080000E 08 UXY i Poisson s ratio EY UXY EX UYX UXY 1 333 0 3330000 SM i mass density e g alum 00025 lb sec 2 in 4 SM 1 00025 0 2500000E 03 ALPHAl i coef thermal exp in merid direction ALPHA1 1 0 0 ALPHA2 i coef thermal exp in circ direction ALPHA2 1 0 0 EPSALW i maximum allowable eff strain percent EPSALW 1 h There is no more help Do your best EPSALW i maximum allowable eff strain percent EPSALW 1 1 6 1 600000 Do you wish to include plasticity in this segment h There is no more help Do your best Do you wish to include plasticity in this segment y Do you wish to include creep in this segment n n Shell wall layer no 1 A stress strain curve the material of this layer must be provided by you if the same material has not appeared in a previous layer
52. updated material properties Use between 3 and 10 usually closer to 3 for best results MAXTRL maximum number of trials at each load level 5 5 ITMAX maximum number of Newton iterations for each trial h ITMAX between 4 and 10 is recommended 6 is a good number ITMAX maximum number of Newton iterations for each trial 6 6 ITIME control 0 or 1 for time increments h ITIME 0 means use time increment s specified in the preprocessor ITIME 1 means use a new time increment ITIME control 0 or 1 for time increments 0 0 Do you wish to force the material to remain elastic h Usual answer is N If you are having numerical difficulty you may want to answer Y Do you wish to force the material to remain elastic n n NOB starting number of circ waves buckling analysis h Make NOB your best current estimate of the critical circumferential wavenumber See pp M12 and M13 for estimates NOB starting number of circ waves buckling analysis 6 NMINB number of circ waves buckling analysis 5 NMAXB number of circ waves buckling analysis 20 INCRB increment in number of circ waves buckling 1 TIME starting time need not be zero in initial run h Note TIME must be less than TMAX see preprocessor TIME starting time need not be zero in initial run 0 0 Do you want stations where plastic flow occurs listed y Y Next give the command BOSORMAIN end of the MAINSE

Runstream - Shell Buckling

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