NASGRO v7.1 Release Notes
Contents
1. r Negative Pin Load Bearing Stress Assumption 1 0 Dit 4 0 Compression Clipping f Kmin lt 0 then Kmin 0 Di2 c lt 05 Full Range use actual values of Kmin Kmax B Implemented two more options for user specified toughness capabilities i e user defined Ke values by crack tip class and constant Kc value EA NASFLA Crack Growth Analysis File Options Tooks Help Epona epa aa yon easar aasma F Oupa F comoutatins Load interaction model Matens parameters Data source NASGRO material fie z Durva views G Baich Data format NASGRO equation constarts C Comperiegha Show hequenthyused matessis kst Search matesiat dota Fieterenge Compare two IDs Add to kequeriiy used materials fat Reload data tom fe f Stat over ECO4 in no restrictions FOR EVALUATION PURPOSES ONLY BR I dad mdtiphcative tacto Material properties ID M7TJ11AB1 7475 47651 PR Sht L T LA DA HHA DW3 5 NaCI UTS Yield Kle Ak 8k Aeg 0 0015 iy 7e s 5 fh fis fams r constants q OKI Di Oh faces fz fos fi foes foi Ch ced in analysis e O throughout C ingia cel value throug Ke values at tips used in analysis F Detouts I User defined by tip class I Constark Ke I User defined by tip location Interice tip Sutace Tip Throughtip Circumferential tip Kie firxte ke Ikte Press F1 for context senskive help F2 for general heip Option 1 defaults Ke values at tips used2. nasmfm xmlz nasmtm xmlz Previously these values were erroneously in US units 17 e When running a multi temperature analysis in NASFLA values of zero for KIc Ak amp Bk are shown for the first material in the out file e Crack case TC18 Corrected Compute cycles to specific crack sizes which didn t work for this crack case e When Comparing two IDs one of the two selected IDs would not be loaded correctly for comparison if a material was already previously loaded into the material input tab e The plot for Comparing two IDs inadvertently displayed K1e for K1c e A flagui exe 32 process remained in memory after the GUI was closed e Crack case CC17 o Provided output of crack aspect ratio al c1 in the out2 file o Modified output format of the initial flaw sizes in the out file to print a c a c al cl and al cl o Fixed an error in geometry limit check for TC23 TC19 transition at cl tip i e W B R lt 24 e Crack case SC08 Incorrect value for initial flaw size c in Geometry Grid when Initial flaw option is set to NASA std NDE using NDE Type Eddy current Fixes NASSIF e Crack case TCO5 corrected the output heading for F4 in the NASSIF output file which was mislabeled F2 e Crack case TC11 hangs resulting from a specific stress gradient used for NASSIF A bug was identified in OPS routines where one of the iterations was stuck in an indefinite loop This root c
3. Crack case SC27 Incorrect symmetric flag written to batchfile was causing the DLL to crash during analysis 20 e Crack cases SC26 SC27 SC28 Updated crack case bitmap images to show both crack tips a and al e Memory leak identified by G95 compiled NASGRO static library A batch job for verification completed with warning indicating memory leaks when using NASGRO static library generated by G95 A memory de allocation bug was identified in the software module to determine stress variations along the net section for embedded slots e Crack case CC14 Incorrect batchfile was created when Two symmetric cracks was selected preventing the run e Crack case CC02 When using 2D Compounding on the GeomTables tab the table selection grids for stress quantities S1 and S3 were missing the yellow background color in the cell of the number of the table being displayed e Inconsistent SIF results from NASFLA and NASSIF analyses using SC26 GUI input decks Inconsistent references in stress quantity index were discovered for CC08 CC13 CC14 CC15 CC18 SC26 SC27 SC28 TC13 TC17 TC18 and TC19 crack models that only had SO and S2 definition with remote loading Fix NASSIF NASCCS e Crack case SC13 GUI crash occurred when choosing Other for Bolt major and minor diameter then clicking the Run button Fix NASFLA NASSIF NASCCS e Crack case TC11 corrected a typo that caused incorrect results when calculating the net
4. 6 35 89mm thk L T LA 7050 T7451 Plt 4 62 102 152mm thk L T LA 7050 T7451 3 8in Plt L T Dry Air 7050 T7451 Plt L T HHA 7050 T7451 Pit L T Salt Fog NACL ASM gt 5 Hz 7050 T7451 Pit T L LA 7050 17451 3 8in Pit T L Dry Air 7050 T7451 Plt T L HHA 7050 17451 Plt S L LA DA HHA FOEN T TAR De T I A A new checkbox for SIF Compouding has been added Do NOT Continue After Transition for users to make a forced choice as to whether or not to continue compounding after transition for those crack cases that have SIF compounding and where post transition compounding is offered Previously there was only the Continue after transition checkbox whose unchecked state meant do not continue but could have been left unknowingly unchecked Now with two mutually exclusive checkboxes the user will be cognizant of the choice made File Options Tools Help kB Geometry b GeomTables Material Ax Load Blocks BulldSchedule FYOutputOptions 7 Computations Comer Cracks v CCO2 quarter elliptical comer crack at hole offset in plate v Save diagram to file Thickness t ie procs cc02 eee C NASAstd NDE Hole diameter D Gh he 4p S 2P Hole ctr offset B M wt Poisson ratio nu W Initial flaw size a B s 6M Initial a c 2 aH Wt P sa E 3 M Dt 0 2 ale 2 0 T Continue after transition I Do NOT continue after transition
5. arc NASBEM would not always calculate the arc properly and at times would utilize points from a previously drawn arc when drawing the arc segment e When changing grid snap values newly created points would snap to the wrong value or alter previously selected points values e When clearing and then creating a new problem NASBEM would not place arc segments correctly Fixes Start Up e The NASGRO license file will now be checked by all GUIs at start up time NASFLA NASSIF NASCCS NASGLS NASMAT NASBEM and NASFORM requiring the version listed in the license file to match that of the GUI itself Fixes User Data Migrator Converter e Data Migrator erroneously put TRADE COMMON NAME STL E into lt file_description gt lt file_description gt tag for User material files when converting pre v7 1 files to XML e User Data Migrator GUI would issue an error message and fail to start if no nasgro ini file existed from a NASGRO installation prior to 7 00 alpha e When converting a pre XML user file to XML format o Incorrect values for material parameters DK1f Fth and Fth were being created o The metric value for a0 was added incorrectly as 0 00381 o For no data in the source file the converter was incorrectly adding a closing record tag 24
6. empty leading cells For these rows the GUI was not recognizing the placeholders for thee empty cells Alloy group descriptions were corrected in NASMFC XMLZ NASMFM XMLZ Appendix G and NASMAT s identify dat file to show the correct MA 1450F 788C 0 5hr heat treatment for ID P3EA13AB1 An internal string conversion error prevented plotting of bi variant stress data The Walker equation material constant values of DKO Rcut A and Rcut were not being saved to input file Linear temperature interpolation problems with user material file 12 NASFLA NASMAT liaison file fitinfo dat NASMAT dataset ID B5BFC2ABO01B1 removed from the list of datasets to plot for the basic fit for NASFLA material BSBFC2AB1 dataset had been erroneously included in an earlier release NASFLA NASMAT liaison file fitinfo dat duplicate and sometimes conflicting entries for NASFLA IDs M7HKI11AB1 P3EDB2AA1 P3EDB2AB1 and Q7AD13AB1 removed NASFLA will now show correct information for comparison plots and references For plotting tension and compression stress gradients an incorrect scriptfile command caused the compression gradient plot to disappear immediately from screen implying this plot was not being generated Crack case SC17 A file handling sharing problem prevented the anaysis from running for the crack transition to CC11 then to TC12 The Scale factors grid associated with the Do parameter anayses grid on the Computations tab was incorrectl
7. for a c gt 1 SC31 Semi Elliptical Surface Crack Offset in Plate Bivariant WF SC31 is a new crack case with the same geometry and stress gradient capabilities as SC19 Compared with SC19 SC31 provides improved solutions for small crack aspect ratios a c lt 1 with longer gauge section length which is consistent with conventional surface crack solutions SC19 and SC31 are identical for a c gt 1 TC24 Through Crack at Center of Plate Displacement Control Developed by ESA NLR TC24 is a counterpart of TC14 It represents a center cracked panel subjected to displacement controlled loading at the remote ends The remote displacement gradient is user specified but is required to be symmetric due to the center crack configuration Not yet implemented in NASCCS or NASGLS TC24 Dj X i 0 1 2 3 00 lt X lt 10 b W 2 0 lt c b 0 95 0 2 L b 10 X x b Transition Capabilities for CC17 e The new stress intensity factor model CC17 for two unequal corner cracks at an offset hole in a plate described above will transition to a new hybrid model HCO1 a corner crack and a through crack at an offset hole in a finite plate subjected to remote tension SO and pin load S3 and then transition again to TC23 two unequal through cracks at an offset hole CC17 can also transition to TC23 directly although this is a less likely occurrence e The new HCO1 model is currently only available as a transition model from C
8. in analysis Defaults J User defined by tip class I Constant Ke User defined by tip location Interior tip Surface Tip Through tip Circumferential tip Kie 1 1Kle Ke Kic Option 2 Kc by tip class Ke values at tips used in analysis I Defaults IV User defined by tip class I Constant Ke I User defined by tip location Interior tip Surface tip Through tip je s fs Option 3 constant Ko Ke values at tips used in analysis I Defaults I User defined by tip class M Constant Ke J User defined by tip location I Kic from input cell IV User defined constant Ke 30 Option 4 Kg by tip location Ke values at tips used in analysis I Defaults I User defined by tip class I Constant Ke IV User defined by tip location clip a tip ctip al tip 56 00 56 00 56 00 56 00 Known Issues in v7 1 Saving New Data to User Material Files The entire NASFLA material data base has been converted to an XML format as discussed above However in v7 1 when specifying a user defined material in NASFLA as New Data it is not yet possible to save a user defined material into the new XML format files e g USRMFC USRMFM etc and the checkbox to do this on the Material screen in NASFLA is grayed out As a work around it is recommended that the user employ NASGRO v7 01 or earlier to save the user defined material data in the old file format and then use the v7 1 Migrate User Data utility available on the NASGRO opening sc
9. section stress caused by limit stress e Crack case CC10 The newly added limit for version 7 10 alpha of 0 lt a t lt 0 9 was incorrectly added as a c not a t e Recast the code for calculating stress intensity factors of crack case SC06 making NASSIF and NASFLA generate identical stress intensity factor results Fixes NASCCS NASGLS e Crack case SC17 the upper limit for a t was changed from 0 9 to 0 95 Fixes NASFLA NASSIF NASCCS NASGLS e Crack case DTO3 data table labels for c tip should be a D1 e Crack cases DTO1 DTO2 DTO3 Entering data in the geometry grid would erroneously gray out the GeomTables tab 21 e Crack case DTO3 plotting of the table data was being prevented e An incorrect break point in the file multi run process was created causing an input file to be flagged as containing bad input when it did not e Using square brackets in the input file name would prevent output files from being corectly copied back from the working direectory after an analysis was complete Fixes NASMAT e In the Enter da dN Delta K tab adding new da dN data for an R value now saves correctly when multiple R values are defined e When saving new da dN data from the Enter da dN Delta K tab to the user file the new data could overwrite previous da dN values for unrelated entries in the user data file e Saving data after pasting from the clipboard to the da dN grid of the Enter da dN Delta K tab caus
10. the Kr result for new failure criteria was requested Crack case TC15 an analysis resulted in the error ERROR TC15_all x coordinates need to end with t A compiler issue was identified where a number restored by multiplication after division was not identical to its original value with a very minute difference Crack case SC17 fixed the crashing problem with t1 t2 capabilities turned on Incorrect batchfile contents regarding the stress gradients for limit stress flags prevented an analysis from running Crack case SC17 a computation with t1 t2 feature and only limit stress check in first load block completed with an error This was a result of variables not being initialized properly Internal coding error prevented the plotting of 1D tabular data IDs for several NASGRO multi temperature material file entries were corrected to properly reflect the temperature in the temperature portion of the ID o MS5BA12LA2 A0013 corrected to MSBA12LA2 A0008 o P3EM23LA2 A0037 corrected to PSEM23LA2 A0008 11 F3KA13LA2 A0007 corrected to F3KA13LA2 A0008 F3KA50LA2 B0007 corrected to F3KASOLA2 B0008 description changed from AISI 316 316L Cast 453F 269C LHe to AISI 316 316L Cast 452F 269C LHe G7AA13LA2 A0007 corrected to G7AA13LA2 A0008 G7CA13LA2 A0007 corrected to G7CA13LA2 A0008 MSBA12LA2 A0013 corrected to MSBA12LA2 A0008 P3EM23LA2 A0007 corrected to P3EM23LA2 A0008 description changed from Ti 6AI 4V ELI RA 1700F 927C
11. 2 0E 8 3 00 0 5 0 5 0 85 2 00 0 1 2 0 0 3 Threshold fanning exponent Cth value used in analysis I7 Suppress closure Qh C Rh C Ointially O throughout Default See Material properties ID M7HJ31AB1 7075 173511 Extr L T LDA UTS Yield Kle Kic Ak a0feg 0 0015 Kth s Kth eg 0 2 7 67 50 a0 fi fi oos o2 Crack growth parameters equation constants c n p q DK Rh Rh Alpha Smav Row f20es 300 fos fos fie fa fois 20 fo3 Threshold fanning exponent Fth value used in analysis Suppress closure C Qh Rh C Ointialy Othroughout New Option puk onl valve Grout Note that when the new F threshold fanning exponent is selected the labels for the threshold parameter cells change to reflect the use of this new model New NASFLA Material Database Format All NASFLA material files have been converted one for one to XML format counterparts e g NASMFC gt NASMFC XMLZ USRMFM gt USRMFM XML etc NASFLA now loads these XML files instead of the pre v7 1 format files Migration of user data files from older installations to the current installation will now include conversion to XML for pre v7 1 user material files In addition the NASGRO GUI Migrate button now offers an option to convert in place but not copy individual pre v7 1 user material files see Help in the User Data Files Migration Utility Improved NASFLA Capabilities for Multiple Temperature Analyses On screen editing of material parameter va
12. 4h Forg 453F 269C LHe to Ti 6Al 4V ELD RA 1700F 927C 4h Forg 452F 269C LHe O O oOoo0o0o o Descriptions for several NASGRO material file entries were corrected to properly reflect the temperature o F3KAS50LA2 from AISI 316 316L Cast 453F 269C LHe to AISI 316 316L Cast 452F 269C LHe o P3EM23LA2 from Ti 6Al 4V ELD RA 1700F 927C 4h Forg 453F 269C LHe to Ti 6Al 4V ELD RA 1700F 927C 4h Forg 452F 269C LHe NASGRO material file entry M2EI11AB1 typo in value for q was corrected from 0 5 to 0 5 Crack case TC23 could not enter data for Set Crack Size Limits option Crack case TC23 blocked transition to crack case TC19 if the B R ratio is larger than 24 Plot titles for saved material data plot images of types cgm and png were missing An internal string conversion error prevented plotting of alternative 2D stress input data An internal string conversion error caused the data file for the exceedance plots for SO for an edited spectrum to erroneously contain hex values preventing the plotting Crack cases CC02 CC04 CC08 fixed the crashing problem when post transition compounding is enabled When mutliple spectrum load blocks are defined their default block types were predefined block but should be manual Copying material data from Excel to the Clipboard then into the 2D material data table caused some data to be copied to the wrong columns in the material table for rows containing
13. C17 The geometry of HCO1 is shown below additional details are provided in Appendix C of the User s Manual t t SotP WY S3 P Dt i i7 So aK Lah DLs Configuration of HC01 New Alternative Threshold Model A new optional introduced in v7 1b to overcome certain difficulties It was observed that use of the present threshold expression in which Ca is set to the NASFLA default of 0 after having been fitted originally with Ca gt 0 in NASMAT causes not only the threshold regions of low R crack growth curves to be shifted leftward or decrease as expected but the threshold regions of high R curves to be shifted leftward as well The alternative threshold expression introduced in v7 1b is free of this problem and is shown below alternative expression for threshold with a new fanning exponent F was p _ fice ptr th 1 R20 1 f R _p 11 F AKa E a R lt 0 1 f R 1 4 th th The current threshold model using Cy is the default once a material is selected in NASFLA on the Material screen The user can choose the new alternative expression for threshold by clicking on Fn in the box labeled Threshold fanning exponent in the GUI as illustrated below Material properties ID M7HJ31AB1 7075 173511 Btr L T LDA UTS Yield Kle Kic Ak 8k a0feg 0 0015 Kthis Kth eg 0 2 77 67 50 fao fi fi fooois 02 Crack growth parameters equation constants n p q DK1 Qh Qh Alpha Smax Flow
14. July 2 2014 NASGRO v7 1 Release Notes New Stress Intensity Factor Models CC16 Single Corner Crack s at an Offset Hole in a Plate Based on Fawaz Andersson solution for remote tension out of plane bending and pin loads It has improved accuracy and a wider geometry range compared to CC02 CC04 and CCO07 and is consistent with the new CC17 solution for two unequal corner cracks CC17 Two Unequal Corner Cracks at an Offset Hole in a Plate Based on Fawaz Andersson solution for remote tension out of plane bending and pin load CC16 CC17 Aten a Tee M k t 4t ee W M M e Gia 1 we W S1 6M Wt C le Sack B 3 P Dt M 2 Dt TYP TTS S r B D 2 gt 2 0 B P W B D 2 gt 2 0 Yi Qi pia A AAE 0 25 lt D t lt 20 0 Defcle 0 2 lt D lt 20 0 2 lt alc lt 5 0 l j t w a 0 2 a4 c4 5 0 OS e725 10 0 0 lt a t lt 0 95 0 lt 2 lt 0 99 i 0 0 lt a t lt 0 95 P D c lt 0 7 if B lt Wi2 2B lt 7 if B gt W 2 Bees 0 9 D c 2B c 0 7 D c4 2 W B c4 lt 0 7 SC30 Semi Elliptical Surface Crack Offset in Plate Univariant WF SC30 is a new crack case with the same geometry and stress gradient capabilities as SC17 Compared with SC17 SC30 provides improved solutions for small crack aspect ratios a c lt 1 with longer gauge section length which is consistent with conventional surface crack solutions SC17 and SC30 are identical
15. SC28 Corrected the features Set Crack Size Limits on Geometry tab and Compute cycles to specific crack sizes on output Options tab to show additional crack tip al previously never shown for non symmetric crack conditions Material parameter fields were populated with incorrect internal record data garbage if that field s tag data was missing from the material file Now if there is no tag data in the file for that field the GUI input field will be blank Attempting to save plots to CGM Postscript GIF or PNG files did not generate an output file The Fth value used in analysis radiobox on the Material tab did not reset to 0 throughout from 0 initially for 3D or 4D crack cases When plotting t1 t2 stress gradients on the Geometry tab the plot dialog window was incorrectly titled as if tension compression stresses were plotted On the Material tab with the New Data data source chosen changing between load interaction models caused GUI elements to be placed incorrectly When loading a DTO02 input file the D2 field on the Geometry Tables was populated with the D1 value from the input file When running multiple input files in batch mode selecting Use material database values when one or more of the input files contained new data as a data source caused a crash Material parameter DKIf was corrected in the NASA metric unit XML material files
16. ause had been identified and resolved The same fix has also been applied to the OPS utility program for NASGRO GUI e Crack case TC11 unmatched column output in OUT1 file for four stress quantities in NASSIF analysis The output format for the fourth stress quantity was incorrectly specified e Crack case SC04 Changing the internal pressure field did not prompt the user to resave the input file e Crack case SC17 incorrect geometry checking code issued a false error for some valid input e Crack case TC11 Crack tip labels for TC11 in NASSIF were made consistent with the updates for crack tip designations from a c to c c1 that were previously made in other modules e A batchfile error during the plotting of the data tables for DT cases stress plotting of SC cases and SIF compounding table data prevented the plots 18 e The upper limit for a t was changed from 0 9 to 0 95 for the following crack cases o C17 SC30 SC31 e Invalid a c and a c output occurred when results were requested for crack sizes larger than the geometry limits The problem was identified because of the change in crack tip designation that resulted when a too large crack triggered a transition A fix to retain the original crack sizes resolved the issue e Crack case CC17 Fixed a problem to make NASSIF run for CC17 with a c equal to 0 2 the lower limit e Crack case CC17 when selecting a fixed corner crack on the Output Options tab the labels of t
17. ed NASMAT to crash e Altering the da dN data on the Enter da dN Delta K tab or on the Examine Edit Data tab selecting a new R value would erase any changes made to any other R value s data set e Pasting da dN data from the clipboard would assign da dN values to other R values rather than the selected R value e Saving multiple fits to both usrmfc xml and usrmfm xml could corrupt the UTS value in the dialog after saving e When saving fits to the NASFLA database in both usrmfc xml and usrmfm xml simultaneously the value of K1c could be converted between units and not converted back or properly emptied leaving an incorrect value of K1c that would appear in subsequent fits The value has now been properly cleared after saving e Resolved a memory access violation triggered on exiting NASMAT Error was previously trapped as it did not affect execution of NASMAT e When attempting to do a NASMAT fit that causes the NASMAT dll to crash the busy cursor icon would persist even after the dll had exited and NASMAT had issued the error and had resumed normal program flow e In the Enter Edit data dialog when selecting Save all R value data to file NASMAT now correctly loads the current save path or the relevant Datafiles directory as the default path rather than defaulting to C e Multiple minor fixes and corrections were made to GUI elements including slight changes to verbiage moving some text to mouse over text small changes to eleme
18. emented crack case CC17 e The capability for the user to provide a problem title and a description is now provided These descriptions are copied to the output file for display and printing Additions NASMAT e Added the following material IDs to the database O CO000000 0 0 B3GE28ABO01A A372 Steel FORG L C M2EA11AB01M 2024 T3 Aluminum 0 25 PLT L T M2EA12AB01C 2024 T3 Aluminum 0 25 PLT T L M2EF11ABO1B 2024 T42 Aluminum 0 125 SHT L T M2EF12AB01A 2024 T42 Aluminum 0 125 SHT T L M2UA31ABO1A 2099 T83 Al Li EXTR L T M2RAI1ABOIC 2198 T8 Aluminum 0 25 PLT L T M2RA12AB01C 2198 T8 Aluminum 0 25 PLT T L M2RA13AB01B 2198 T8 Aluminum 0 25 PLT TL45 M7TF11AB01U 7475 T7351 Aluminum 3 PLT L T M7TF12ABO1E 7475 T7351 Aluminum 3 PLT T L e Added the following material IDs to the fatigue crack growth and toughness database O OJEE O E e O O E O O E O O B2IBA1AB01A A225 Grd B Weld L C RT B2IBA7AB01A A225 Grd B Weld HAZ L C RT B2IB18AB01A A225 Grd B PLT L C RT B2IB18AB01B A225 Grd B PLT L C RT B2IB18AB01C A225 Grd B PLT L C RT B2IB18AB08A A225 Grd B PLT L C 20F E2FB11AB08A AOS1146A PLT L T 20F E2FB12AB01A AOS1146A PLT T L RT E2FB12AB01B AOS1146A PLT L T RT E2FB12AB01C AOS1146A PLT T L RT e NASMAT now allows users to specify plot limits when plotting raw material data Changes NASFLA e Crack case SC08 added Eddy Current to available NDE meth
19. ent data Attempting to plot the SIF Compounding table data on the GeomTables tab would at times result in various intermittent errors including a GUI crash DLL errors and individual instead of combined interpolated data plots due to the GUI improperly indexing the various stress quantities defined for the chosen crack case Changing the interpolation type for a SIF Compounding table would cause a GUI crash Crack case TC11 Incorrect indexing of crack tip SIF compounding tables led to a GUI issued error message stating some SIF tables were undefined For stress quantities S2 and S3 if two or more SIF compounding tables were defined and saved in the input file only the first one was being loaded Crack case SC26 an error in geometry grid indexing incorrectly determined 2D cracks to be 3D resulting in the SIF Compounding checkbox to be removed from the Geometry tab and an erroneous batchfile preventing the analysis from running Inconsistent SC17 SC19 and SC30 SC31 results for crack models subjected to simple remote tension Insufficient refinement in point spacing for generating reference solutions with smaller a c ratios was identified to be the root cause Changing to more refined point spacing resolved the inconsistency Steep stress gradient failed OPS algorithm The steep stress gradient with maximum stress along one single line appeared misleading the contour based 2D OPS algorithm A revision was made to resolve this issue
20. evelopment team is investigating solutions to this complicated output issue Net Section Yield NSY Residual Strength Calculation for Weight Function WF Models The NSY residual strength calculations plots for WF models are incorrect when one or more stress gradients are input The NSY failure mode calculation for WF models is correct during the NASFLA crack growth analyses The WF model G G factors printed in the out2 file are incorrect since they are computed for remote or uniform constant loadings and not the input stress gradients they are only used in plotting the residual strength NSY curve At present the approach to take for a WF model residual strength analysis would be to use the Limit Stress option on the Load Blocks page and specify the peak stress of the gradient for each applicable stress component The NASGRO development team is investigating solutions to this issue Additions NASFLA e Crack growth constants for the following materials were added to the materials files B2IB18AB1 A225 Grd B PLT L C Lab air RT B2IBI18AB8 A225 Grd B PLT L C Lab air 20F B2IBAIABI1 A225 Grd B Weld RT B2IBA7AB1 A225 Grd B Weld HAZ RT B3GE28AC1 A372 Cls V Forging L C Dry air RT E2FBI11AB8 AOS 1146A PLT L T Lab air 20F E2FB13ABI1 AOS 1146A PLT L T amp T L Lab air RT M2UA31AB1 2099 T83 Extrusion L T Lab air RT M2UA32ABI1 2099 T83 Extrusion T L Lab air RT O OOO O On OOO 7 Addition NASSIF e Impl
21. g Osgood tags no longer nested in separate RambergOsgood grouping e XML material files Alternative Failure Criteria tags no longer nested in separate AltFailureCriteria grouping e Crack case CC17 Simplified the limits expressions in the bitmap image Change NASSIF e Crack cases SS02 SS03 SS04 SSO5 SS06 SS12 the output files for these standard specimen cases now contain the value of the pin load P in addition to the mean bearing traction applied by P to the specimen e Crack case CC17 Simplified the limits expressions in the bitmap image Changes NASFLA NASSIF NASCCS e Crack case TC23 Two unequal through craks at offset hole o Extended the solution to handle B gt W 2 and or b gt W 2 where B is the distance from the hole center to the plate edge and b is the distance from the center of the overall flaw tip to tip crack to the plate edge and W is the width of the plate o Provided the two pin load options for the crack case i e compression clipping and full range e For HCO1 o The lower c cl limit is extended from 0 1 down to 0 01 and Appendix C updated accordingly o The stress intensity factors at cl tip are multiplied by a factor 1 05 to better calibrate the FEA benchmarks e Crack case TC23 The bitmap image has been reversed horizontally Changes NASFLA NASSIF NASCCS NASGLS e Removed the following Reserved for future use crack case menu selections CC06 EC03 SC16 e Inf
22. he controls for entering data for the other crack were incorrect a c flaw sizes a auto fill a c auto fill a e Saving plots to text files from the Computations tab triggered a crash e Crack case TC18 Inconsistent output for user provided stresses The load description indicated remote tension and bending while the input deck contained users provided stress gradients defined along the crack plane The inconsistency was a result of incorrect output flag in implementation e Crack case CC14 Initial flaw size a was erroneously being shown in the Geometry Grid causing the entry to be required and prevented the analysis from running e The category list for Embedded Cracks contained an extraneous blank line at the end Fixes NASCCS e Changing units setting would cause a GUI crash e In batch mode for sequential analyses of crack cases SS19 and SSO1 an incorrect error message was displayed suspending the batch run e Crack case SC15 The error message Solution invalid if a c lt 0 1 or a c gt 1 21 was erroneously generated for valid values of a c preventing the run e Crack cases SC30 SC31 The descriptions on the Geometry tab stated semi elliptical surface crack at offset hole in plate rather than semi elliptical surface crack offset in plate Fixes NASFLA NASSIF e Crack case TC11 An unspecified stress variation in full range for non symmetrical crack case resulted in mi
23. lues has now been extended to multi temperature material file entries Implemented the capabilities of user specified unique limit stress temperature in multiple temperature fatigue life analysis New failure criteria enabled with temperature effects The enabled new failure criteria now will check the following and work accordingly o Temperature dependent properties o Tension compression or t1 t2 stress gradients o Limit stress with t1 t2 and temperature dependency When loading an input file for single temperature materials the GUI will now compare the values of the material parameters stored in the input file with the values in the material file for the loaded ID If any value differs a notification will be displayed allowing the user to choose to retain the loaded input file values or to use the material file values for the analysis For batch mode running multiple input files at once a new message dialog is presented at the start of the run to present the user with this choice Use input files values or Use material file values can be chosen and this decision will be applied to all input files in the run that contain these differences New NASFLA GUI Features e The Enter ID code directly button on NAFLA GUI material input page has been relabelled to Search material database Button s search functionality now includes IDs as before as well as any material entry s text description field using a search string of at lea
24. m Computations to Material then back to Computations When visualizing the GSFC spectrum on the Load Blocks tab the Using stress level histograms radiobox option did not plot Switching between elasticity types did not clear all controls from the Material tab Full cyclic shakedown analysis fails to complete with Fortran error code A bug was identified in cyclic shakedown routines when to retrieve the elastic stress state from the backup file NASFLA did not generate a plot for da dN in cases where dal dN existed in the out2 file NASFLA did not disable Advanced Spectrum Editing when using multi temperature data or incompatible load interaction models Furthermore when switching from Strip Yield to an 16 incompatible interaction model or switching to multi temperature data when Advanced Spectrum Editing was already selected NASLFA did not disable ASE in existing load blocks NASFLA did not perform validation for the Threshold Material parameters Alpha and Smax Flow Crack case SC27 Incorrect symmetry flag was written to batchfile preventing the run Crack case SC26 User provided NASFLA input deck crashes the stand alone NASFLA code An error was identified in the designation of offset when invoking the SC17 SIF routine from SC26 crack module Crack case SC28 Computations failed due to an error in the designation of offset in SC28 crack module Crack cases SC26 SC27
25. nd Threshold Smax Flow were editable in the NASFLA GUI but their edited values were not written to the batch file Reinstated IDs PBEMD2AB1 PBEMD2LA4 PBEMD8AB1 PBEMD8LA4 were removed in v601 and v610 due to digitizing and fitting errors On the Material tab the Material Parameters label would not retain the value The parameter values shown have been changed from their original material file values when changing between temperature values in multi temperature data Crack case CC17 data column al cl was added to the out2 file and the NASFLA GUI was expanded to view and plot this data Crack case CC17 If the analysis transitioned to HCO1 an error message was issued when viewing output details stating this crack case was not recognized Crack cases BE02 03 CC17 EC02 04 05 SC17 18 19 26 27 28 30 31 TC11 23 When viewing the output column headers for Beta Factors F for crack tips tips al and cl were missing Saving plots to text files from the Plot Dialog caused a crash Crack case TC18 A Fortran error code 5 occurred when running TC18 with two symmetric cracks It was caused by an incorrect implementation that restricted the number of stress quantities The Curvefit views radiobox was inadvertently displayed when changing the Temperature to view listbox for user multi temperature material data During computations using User 2D tabular material data the NASFLA GUI briefly changed the selected tab fro
26. nd can no longer be called from NASFORM As such Wordpad has been removed from the NASFORM menu Change User Data Migrator Converter e Bracketed ID data is no longer written to the beginning of the material description tags during file conversion 10 Changes Configuration Control Updated to include new crack cases new Fth related threshold parameters Readability improvements in the available and unavailable crack case lists Compiler Changes NASBEM and NASFORM have been recompiled under Visual Studio 2008 Fixes NASFLA Crack case SC19 when transitioning to crack case TC11 the transition message that was issued was confusing The crack tip labeling for TC11 has been changed to be consistent with the surface tip designation used for SC19 An internal memory problem caused the selections for the Load interaction model radiobox to somteimes become blank Crack case SC06 solution was modified to better match NASSIF Previously NASFLA calculated much smaller stress intensity factors than NASSIF for short cracks Differences exist between NASFLA and NASSIF for SC06 due to solution speed considerations in NASFLA Missing drivers and font files caused the material plot of the Compare Two IDs feature to contain no text Crack case SC17 an input deck causes GUI to terminate the computations with no results The error was a result of a symmetric SC17 transitioning into a symmetric TC11 where printing
27. nt size or position in order to correctly align elements or add in separators or borders between elements 22 e When viewing references clicking the Sort by Name or Sort by Number buttons without first selecting a set of references to view crashed NASMAT A warning dialog will now be issued to inform users to first select a reference if none has been selected before sorting e When viewing the Recent Changes in NASMAT some lines from the Changes txt file were not being displayed properly e Lengthy filepaths to the NASMAT Datafiles directory would occasionally cause NASMAT to display incorrect behavior or crash e When saving fits to NASFLA NASMAT would not properly fill the MatIDProdForm XML field nor correctly handle reserved XML characters e Corrected digitized data for IDs P3EMD2AB01A P3EMD2LA04A P3EMD8ABO0IA P3EMD8LA04A e The C value was erroneously truncated to a single decimal place when saving fits to the NASFLA user material file e The NASA material file ID s E2FB12ABO1A and E2FB12ABOIC did not display R values e Deleting User material ID s from the Data Identification tab via the right click command displayed erroneous warning messages about the NASA data files did not fully delete the chosen ID from the header and data files and did not refresh the ID list after the delete e When saving fits to the NASFLA user material file the DescriptionO tag Legacy Material File name and the Ver
28. ods e The threshold value of Smax Flow stress is now read from the materials file and displayed allowing the user to modify its value if the user wishes This can be done for both single temperature and multi temperature cases e Crack growth constants for the following materials were modified in the materials files O O O E4EB29AB1 Pyrowear 52 5 Rnd Bar R L Lab air RT E4EB29AC1 Pyrowear 52 5 Rnd Bar R L Dry air RT M7TF12AB1 7475 T7351 PLT T L Lab air RT e Re enabled the New Data Data Source on the Material tab e Crack case BEO3 applied the beta factor correction in calculation of stress intensity factor range for a tip and c tip e Pre v7 1 user material files that were migrated and converted to XML now allow using the same sequence of alphanumeric characters to represent different combinations of product form environment orientation in their material ID e Removed the following controls from the NASFLA GUI for elastic plastic mode only o Show list of frequently used schedules and Add schedule to frequently used list buttons on the Build Schedule tab since these were already non functional o Compute cycles to specific crack sizes checkbox on the Ouput Options tab a feature for linear elastic mode only o View Output Summary button on the Computations tab which was not needed since the output window is already populated automatically upon completion of calculations e XML material files Ramber
29. ormative popup messages added to the following crack cases CC02 CC04 CC07 CC16 SC17 SC19 e For batch mode analyses using Create batchfiles only mode batchfiles formerly written to the single directory MultipleFilesBatchDirectory in the data files installation path will now be created in the directory in which the input files are located Change NASFLA NASCCS e Crack cases CC08 CC10 The surface correction factors B have been enabled and applied to both surface crack tips Changes NASMAT e The plot dialog has been redesigned to allow changing the plot label and the X Y ranges from the dialog box once a fit has been performed The ability to manipulate the X and Y ranges is not enabled for plotting only the raw data e Saving user fits to the user file for NASFLA usrmfc xml and usrmfm xml has been changed to handle the new XML format e When saving R value data to file through the Enter Edit dialog NASMAT will now automatically suggest a file name based on the material ID and generate a prompt for the user if the file already exists e On the Curvefit Plot tab the plot range text boxes have been reordered The X minimum and maximum boxes are now grouped together as are the Y minimum and maximum boxes e Saving fits to NASFLA NASMAT no longer inserts bracketed ID s into the material description fields Change NASFORM e Wordpad has been removed from the Windows default path as of Windows 7 a
30. rack Case CC16 an incorrect geometry error was issued for the two symmetric cracks configuration The material parameter Threshold Smax Flow was not being saved to nor loaded from input file On the Load Blocks tab the screen label for entering limit stress seen after checking the Check throughout this block for crack instability and net section failure at limit stress checkbox was corrected to be Scale factor s for limit stresses for the following crack cases and crack plane stress definitions o SC17 Polynomial SC17 User input Crack Plane SC30 Polynomial SC30 User Input Crack plane EC02 User Input Crack plane EC04 Polynomial EC04 User input ECO5 User input Crack plane O10 O OLOO The expression upper limit for a t was changed from 0 9 to 0 95 for the following crack cases SC17 SC19 SC30 SC31 The second title line of the plot showing a material s Basic fit has been corrected to show the complete Detailed description of the material which includes the alloy description When displaying entries from metric multi temperature materials files values displayed in the View temperature dropdown box were incorrect for both values displayed F and C The program reads a single temperature value from file in F or C depending on which Units selected in the options but then incorrectly calculated the values to display 15 The four material parameters Alpha Smax Flow Threshold Alpha a
31. reen to convert the user material files to the new v7 1 XML format An alternative work around would be to use an XML editor or a plain text editor to edit the v7 1 XML format user files directly Please consult Appendix E for more information on the new material file format A future version of NASGRO will have the capability to save user defined material data to the XML format database Post Transition Crack Tip Output in Out2 File When multi degree of freedom MDOF crack models having two or more crack tips automatically transition to other crack cases the printed crack lengths in the out2 file can sometimes be difficult to interpret This is because the out2 file is printed based on the crack tip labels of the pre transition crack case After transition when the type and number of crack tips has changed data may be printed in the wrong columns or mislabeled because the numbers of data columns before and after transition do not match but all the data are in fact printed The real problem is that the crack tip nomenclature genuinely changes from crack case to crack case and it is difficult to anticipate in advance what kind of transition will occur This is a common problem that has existed for some time in earlier versions of NASGRO and it is not specific to any particular crack case At present the user needs to carefully examine the post transition crack lengths in order to be clear in the interpretation of the results The NASGRO d
32. rison fits and changed the format of the displayed material parameters and their values to be a two column display for better readability and to avoid some of these labels from crossing the right edge of the plot 13 Crack cases SC09 SC10 corrected multiplication error in the formula for converting between US and metric units for calculating initial crack depth when using a bolt size of Other and the NASA std NDE initial flaw size option Corrected legend for Fl a for post processing plot of beta factors which incorrectly read FO a Unchecking the Suppress closure checkbox did not re display the material parameter Smax Flow Crack case SC27 If crack case TC15 was previously selected then crack case SC27 the Set crack size limits checkbox was misplaced on screen and would overlap the Geometry Grid For the Compare Two IDs button whole number values of some material parameters were being incorrectly interpreted by the plotting program as integers resulting in incorrectly calculated values and preventing the plot Plots using the Compare Two IDs button of a material description containing a double quote failed due to incorrect creation of the plot scriptfile Crack cases CC16 CC17 corrected a problem in plastic zone size calculation to make the two crack cases work with the Willenborg retardation models A problem with truncation of alloy descriptions when reading the user s material file was fixed in
33. sion tag fields were empty instead of containing no legacy material file data added after adoption of XML and the current NASMAT version number e When fitting DkO Dk1 and Cth via the Curvefit Plot tab the Threshold Parameters plot dialogue did not display the X and Y axis names R and DKth on the plot dialogue nor properly set the default plot limits e Entering data via the Data Source button on the Enter da dN Delta K tab did not automatically display the newly entered data on the Enter da dN Delta K tab Fixes NASGLS e Corrected the Recent Changes list removing the extraneous Added banner which had no associated items and included the missing Changed title which did have associated items e Crack case CC07 The NASGLS GUI contained incorrect values for the lower limits of the solution validity expressions for a c and D t for a case with stress quantity S1 defined e NASGLS DLL error when trying to run cases with database input material The root causes were twofold One was a result of multiple uninitialized variables such that the stand alone 23 wouldn t work The other was resulting from the dynamic file ID not being passed correctly The bug fix has resolved both issues Fixes NASBEM e When calculating midpoints for segments NASBEM would calculate the incorrect point or utilize an incorrect level of accuracy if snap values had been altered e When creating a circular
34. sleading results The new implementation now performs two checks for stress gradients provided for the univariant crack models CC08 CC11 CC13 CC14 CC15 EC02 EC05 SC17 SC18 SC30 SC26 SC27 SC28 TC11 TC12 TC13 TC17 TC18 and TC19 One is to ensure the normalized coordinates are in ascending order and the other is to confirm the stress points are given over the full range 19 Crack case SC18 the limit on a T of 0 8 was exceeded during fatigue crack growth calculation This limit has been extended to 0 9 The new limit is applied to both NASSIF and NASFLA analyses for consistency Similar changes are also applied to the CC10 CC14 SC18 and SC27 crack models A bad internal file path prevented the compounding data from a previous analysis run to be viewed Crack case TC11 consistent crack tip labeling has been imposed such that the crack tips are described by c and cl tips instead of a and c tips This change is crucial to help clarify when crack transition from SC17 to TC11 occurs where the old crack tip designations may confuse the user by the changes of crack tips from c and cl tips of SC17 to a and c tips of TC11 Crack case CC12 errors in SIF calculations were found in cases where a c is slightly lower than 1 A bug was identified in the pre integration tables for CC12 New tabulated routines have been implemented to resolve this issue Crack case SC06 corrected a batchfile error preventing the plotting of stress gradi
35. st 3 characters From the search results list any single entry matching the search term can be loaded into the material input page for use in analysis or be examined graphically or any pair of entries matching the search term can be compared graphically The drill down method of searching through categories alloy groups etc of prior NASGRO versions is also still available by clicking on Show materials list File Options Tools Help Bl Geometry p GeomTabes L T Material w Load Blocks AxBulldSchedule FYOutputOptions 47 Computations r Load interaction model _ Material parameters Non Interaction Data source NASGRO material file v C Constant Closure Daa format Nas E c zed Wil mat NASGRO equation constants Chang Willenborg Show materials list Show frequently used materials list Search material database C Strip Yield Compare two IDs Search Heb Search results for 7050 46 records found Click to select or unselect records one or two 7050 T6 Sht T L DA 7050 T6 Sht T L HHA 7050 17351 Pit L T LA amp DA 7050 17351 Pit L T HHA 7050 17351 Pit T L LA 7050 T7351 Pit T L HHA 7050 T7351 Plt S L DA 7050 T7351 Pit S L HHA 7050 T73511 Eer L T DA LA HHA 7050 T73511 Etr T L DA LA HHA 7050 174 T736 Forg L T LA 7050 174 T736 Forg T L LA 7050 174 T736 Forg S L LA 7050 17451 Pit 0 25 3 5
36. the out1 output file displayed in the GUI output window after calculations are complete The material description as displayed on the Material tab just above the material parameter text boxes was excessively truncated and was not using all the available screen width This has been extended to use the entire screen width to display as much of the material description as possible in most cases the description is displayed in its entirety Crack case SC19 error produced using SO S1 and RS stress gradients A compiler issue was identified where closed files having been assigned negative file IDs triggered the error The related routines have been modified to fix this problem Crack case SC30 The symmetrical crack configuration was not working with the strip yield load interaction model The current strip yield load interaction model can support up to two crack tips and in this case this load interaction model should remain applicable The error was identified due to a bug that didn t include SC30 as one of the valid crack models for strip yield model The strip yield routines have been updated to include this new crack case Enabling Keac check for multiple temperature applications resulted in immediate failure even when the computed SIF was smaller than the specified Keac The root cause was because the Keac specification was only initialized with the first temperature while the Keac values with the rest of the temperatures were not Assigning
37. the provided Keac value to the rest of the temperatures resolves the bug Analyses using 2D tabular material data could not be run This was caused by an internal storage array being too small for the data that is loaded from input file The GUI input file now stores the entire material record in XML format The array size used to read this very long string was 14 increased in 7 10 alpha from 1000 to 15 000 characters however for some very large tabular data the new size limit was still exceeded and so was raised again to 100 000 Crack case TC16 An additional run time edit check has been added u a measure of the stiffener stiffness relative to the sheet stiffness where u As Es As Es L t E must be within the range 0 1 0 5 The Load interaction model radiobox was inadvertently shown in the NASFLA GUI in elastic plastic mode and has been removed The Bypass NSS checkbox was inadvertently shown in the NASFLA GUI for elastic plastic mode Crack case TC17 different result obtained using the standalone code with instability check at limit stress The NASGRO GUI predicted immediate failure due to K limit larger than Ke while the standalone predicted the computed K exceeded Keac at 182 563 cycles The inconsistency was due to a bug in the program that was picked up by the compiler used to generate the stand alone code resulting in very large negative K limit value The related routine was modified to resolve this C
38. y located too far right on the GUI page preventing it from being seen Using Chang Willenborg crack growth model caused the stand alone code to crash due to two uninitialized variables Batchfile content error for reverse calculation analysis in some instances prevented the analysis from running This would happen if the compute cycles to intermediate crack size checkbox was checked in calculate crack growth mode then the mode is changed to calculate initial flaw size given target life reverse calculation mode For the Generalized Willenborg load inteaction model the Select Willenborg Model radiobox was always being set to the first choice preventing the second choice and its associated Parameter PhO value from being selected entered or saved to inpuf file Internal buffers that were not cleared caused some stress grids to be erroneously shown on screen Loading an input file with only saved material data caused a Configuration Control error message regarding the crack case being loaded even if no configuration control restrictions were in place Additionally the material data was not loaded Crack case TC23 The option to continue compounding after transition has been enabled Numeric validation of the contents of the 1D table containing threshold parameters has been corrected to properly flag non numeric entries Included missing title lines and increased width of plot area image when viewing material Basic and Compa
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