NASGRO v7.0 Release Notes
Contents
1. Crack case SC17 an inconsistent designation for bending during remote tension bending or polynomial stressing led to too small a value for Lr for FAD option 1 This has been corrected 11 Crack case EC05 An incomplete calculation for crack tips computed Kr values caused an improper program exit during an analysis resulting in termination and a non specific error message Crack case TC11 Incorrect failure criteria code used in computation for symmetric cracks caused computations to fail immediately This has been corrected Corrected the legend entry when viewing output plot data for beta factor Fl a which erroneously read FO a Crack case SC18 the residual stress checkbox was not being redisplayed when shakedown option was turned off Crack case TC15 corrected internal condition preventing some analyses from running For analyses using the Strip Yield load interaction model the value for the fast run output option difference for Sopen values to be deemed stable was not being written to the batchfile properly preventing the run Corrected a memory error with Optimum Point Spacing for cyclic shakedown Crack case CC14 Enabled the Strip Yield load interaction model to work properly with this crack case Crack case SC28 an error in writing crack size data to batchfile caused incorrect results Several individual material parameter fields were shown on the Material tab inadvertently as a result of2. do not delete subfolder to excel_templates In addition upon opening the worksheet the cell containing the location of where all generated input and output files will be saved is now pre filled with the Excel file s location As in previous versions this can be changed by the user or left blank in which case the location defaults to the user s desktop 23
3. the batch file creation routines in version 7 00 alpha introduced problems which prevented analyses from running Crack cases CC08 SC18 Corrected a batch file error that prevented older pre 7 00 alpha input files from running if the stress distribution selected was Remote tension NASMAT Fixes Made corrections to fix the following errors noted when using the Spline option to perform a Curve Fit and Plot Fit lines were being displayed for all but one of the data sets being curve fit The Add Sort option in the Values from spline fit window displayed erroneous values of DeltaK for user entered values of da dN This feature is presently disabled The Print Table option in the Values from spline fit window did not function and instead triggered an error message The Print Report option in the Values from spline fit window did not function and instead triggered an error message Corrected a formatting error with M2IFI2ABO1E1 M2IF12ABO1E1 now properly displays data Adding a da dN value to Spline fit was disabled Spline fit altered to correctly graph all R values Fixed the Save Changes button on the Examine Edit dialogue to prevent occasional crash to desktop Fixed crash from placing the NASMAT data files in a long file path 20 Corrected write all data behavior in Examine Edit pane to prevent writing of extraneous data values at end of file when switching between multiple material IDs Corrected iss
4. and CC07 two crack solution 0 2 lt ac lt 2 0 1 0 lt D4 lt 40 D 2 c B lt 0 5 o CC07 one crack solution without bending 0 1 lt a c lt 2 0 0 5 lt Dit lt 4 0 o CC07 one crack solution with bending 0 2 lt ac lt 2 0 1 0 lt Dit lt 4 0 D 2 c B lt 0 5 Corrected a problem that occurred during batch mode processing where a single input file containing bad data would stop the entire batch process b 1371 Crack case SC07 the zone of validity was changed to a lt 0 5 D making it correspond to the domain for which numerical results are available in the source document for this solution b 1406 Fixes NASGLS Crack cases CC08 TC13 For the crack plane stress definition selection of Tension bend corrected the Load Blocks tab stress quantities displayed to properly show SO and S2 instead of only SO Crack case CC08 The addition of bending stress S2 and subsequent rewriting of the batch file creation routines in version 7 00 alpha introduced problems which prevented analyses from running 19 NASCCS Fixes Changing the value in Critical SIF text field did not prompt to re save the input file Crack cases CC08 SC18 TC13 For the crack plane stress definition selection of Tension bend corrected the Output Options tab Applied Stresses labels to properly show SO S2 instead of SO S1 Crack cases CC08 SC18 The addition of bending stress S2 and subsequent rewriting of
5. e Removed inadvertent characters shown in the out2 file when stress gradients at common point spacing are displayed e While running NASSIF the number of data pairs under the USER DEFINED stress gradients label in the OUT1 was inconsistent with the number of data pairs in the input deck The scenario occurred only when the user defined stress gradients contained two stress data pairs e Crack case CC02 Plot table data buttons for 2D SIF Compounding were not removed from screen when changing from 1D SIF Compounding to 2D SIF Compounding Woe e The column output for step number contained in the OUT2 file had an x instead of showing its numerical step wise values e SIF Compounding controls were inadvertently turned on in the GUI when a geometry grid entry was edited causing an invalid batchfile format which prevented the analysis from running Fixes NASFLA NASSIF amp NASCCS e For crack case CCO7 one crack solution o Corrected a data error in the fundamental geometry factor table for pin load changing the data value from 6 0 to 0 5512 18 o Corrected a coding error in the calculation of geometry factor F3 under pin load Crack Case SC05 Changed geometry check expressing it in terms of D t instead of t Dmean The accuracy limiting bound on D t was changed to 4 0 exactly For crack cases CC02 CC04 and CC07 the following ranges of applicability were verified and are now displayed in the GUI o CC02 CC04
6. lists for each previous NASGRO release In addition a new single overall list containing the changes for all previous NASGRO releases as well as the current release has been created Fixes Configuration Control If any non default values were entered for the fields for the fields a0 Kth ratio or Cth option the Remove all restrictions button would not reset these fields to their default values At that point a standard no restrictions NASFLA configuration control file could not be created unless the Configuration Control GUI was closed then restarted Fixes Manual Corrected link in User Manual Table of Contents for Appendix U which was incorrectly linked to Appendix V 22 Linking Excel to NASFLA NASGRO v6 2 was released with several Excel files each of which contained a worksheet customized to accept input for a particular NASGRO crack case TCO1 TC03 TCO5 and SCO1 For NASGRO v7 0 these worksheets have been combined into a single Excel file located in the nasfla excel_templates subfolder of the data files installation location For example if the NASGRO data files are installed in C Documents and Settings username My Documents nasgro7 0 then the Excel file would be installed in C Documents and Settings username My Documents nasgro7 0 nasfla excel_templates In addition for safe keeping the data files installation procedure puts a copy of this file in the Archived originals
7. speed choice Select Willenborg Model Closure factor CFspec computed from Through crack toughness computed from Properly relabeled the View Output button on the Computations tab after an analysis has been re run with changed input to read Show selected details if any detail selections were made prior to the re run Corrected inadvertent data written to batchfile that prevented some analyses from running When plotting material comparison fits the Quit button did not end the plot functionality as intended and all subsequent material comparison plots would still be prompted for viewing Fixed a bug in SC05 TC08 transition to convert crack size c due to different definitions of the crack size in the two crack cases Corrected a problem with commentary lines in the out2 file which caused the GUI to crash when selecting all details to show after calculations have completed The button Compare two IDs was being incorrectly shown on the Material tab for Elastic Plastic mode This functionality applies only to Linear Elastic mode The error Some material parameters not defined cannot plot would be shown when loading an input file that did not contain any material data Post processing plot of Residual Strength by NSY was incomplete for some analyses containing crack transitions 13 e An error in the spectrum editing functions caused an incorrect number of cycles to be written to the last line of the edited file w
8. NASGRO v7 0 Release Notes NASFLA Additions New Stress Intensity Factor Models also in NASSIF CC13 Corner Crack at Edge Notch in Plate SC26 Surface Crack at Edge Notch in Plate November 26 2012 o These univariant weight function stress intensity factor SIF solutions are valid for a corner and surface crack at the tip of an edge notch of arbitrary shape and are extensions of TC17 Two common types of notch shape are supported in the GUI an angular straight edge notch and an elliptical notch for a very wide range Stresses can be applied as remote tension in plane bending or un cracked crack plane stresses of geometry parameters cC13 4 0 2 lt amp lt 5 B 0 lt lt 07 W 0 75 lt __ 0 96 W B e OsB lt e a lt t lt 0 95 i 0 1 2 3 e1 025555 o lt 8 s 0 75 cCc13 re So 28 y osd s24 ce s T i 0 1 2 3 29 r jeder Laa Iie ec C26 sey Stttttttt 0580575 lt dir lt a o lt St lt 0 75 28 r oss y c lt gyo 08 Sitti s pee 01s Isos a lt Z lt 095 Tai 2 lt 095 28 r T e CC14 Corner Crack s at Offset Embedded Slot or Elliptical Hole in Plate e SC27 Surface Crack at Offset Embedded Slot or Elliptical Hole in Plate o These univariant weight function SIF solutions are for corner and surface cracks or two symmetrical cracks at the notch tip s of an offset embedded slot or elliptical hole in a plate and are extensio
9. S 1 Material ya oad Blocks BulaSchedule fF YOutputOptions 7 Computations Problem title optional I Problem description optional Frequency of wrting data to output fles p Intervals schedule block step intervals Schedule interval for end of schedule output 0 final results only 1 crack growth intervals Note a non zero schedule interval gives access to finer control of output frequency Block interval for end of block output 0 no end of block results 1 I Compute cycles to specific crack sizes Block interval for printing output within block 0 no detailed output within blocks 0 A C User defined limits for post processing plotting of a second variable may now be entered Users may now add custom plot tiles to all plots graphs For all plotting the default plot axes limits will now be displayed on screen prior to the generation of the plot image If there are numeric limits from the material database those will be shown If the limits are based on computed data asterisks will be shown Appended bracketed text to NASFLA GUI title bar indicating the current status of the configuration control restrictions no restrictions or configuration controlled When both shakedown and limit stress checking are selected the limit stresses will now take into account the residual stresses from shakedown Provided output of the sorted iteration table in the NASFLA inverse calculati
10. conel X 750 ID Q3SD26LA2 The Computations tab Save window contents to doc file button would be permanently disabled if the Do parameter analysis checkbox was checked Removed Input SIF Comp as a selection on the Computation tab s Select output to view listbox whenever SIF Compounding was used in the analysis This separate outlfile display choice interrupted the display of Initial crack size as part of the Input Geometry data display Removing Input SIF Comp allows both the SIF compounding outlfile data and the initial crack size outlfile data to both be properly displayed when Input Geometry is selected Shakedown GUI controls text label and entry grid were not removed from the Material tab when Shakedown option was set to None Crack case SC19 corrected typo in geometry error for a c upper limit While the GUI correctly disallowed ratios greater than 8 0 the warning message erroneously stated 0 8 as the upper limit Crack case BE02 Corrected tip designation for Material tab s Kc value at tips fields from a tip and c tip to c tip and cl tip Crack cases SC17 SC18 TC11 Material tab fields Kc values at tips which previously always showed the number of tips for the non symmetric states will now be updated to also show the correct number of tips for the symmetric states Major overhaul of the monotonic and cyclic shakedown algorithms was required due to incorrect performance of shakedown feature
11. er dimension D formerly blank will now default to a value of 1 Removed crack case DT04 Crack case SC13 Corrected the geometry check for solution inaccuracy for r D outside the range 0 005 1 0 This check which was added in NASGRO version 6 12 did not correctly handle all formats of the major diameter D as displayed in the Bolt major and minor diameter selection list Crack case SC04 Changed output text clarifying it to distinguish the hoop stress effect of internal pressure from the cumulative effect of the hoop stress and the direct crack opening effect Crack cases CC02 CC04 CC07 Refined solution limits and added dynamic bitmap display based on number of flaws selected CC02 CC07 Updated various bitmaps for weight function crack cases to specifically show the independent dimensional and non dimensional coordinates and additional expressions for limits When checking throughout a block for crack instability and net section failure at limit stress the on screen text of limit stress for stress quantity has been changed to scale factors for limit stresses when crack plane stresses are specified 10 NASFLA Fixes The following corrections have been made to the materials files Removed duplicate entries for Jethane M152 ID L6AB28AB1 Corrected the value of Bk for 7050 T7451 IDs M7GJ11AC1 amp M7GJ12AC1 Corrected the value of n for 7475 T761 ID M7TI11AB1 Corrected the value of C for In
12. esent In version 7 0 a check was implemented such that if a flat load step is detected a warning will be printed but the computation will continue e When plotting a material Basic Fit the on screen value of Kc will now be shown with one decimal place and also display the average thickness value on which it is based Changes NASSIF e Crack case TC13 Optimum point spacing will now always be used when selecting Tension bend for crack plane stress definition Changes NASCCS e Clarified the following field labels on the Output Options tab o Critical SIF changed to Fracture toughness o Critical stress changed to Yield or flow stress o Enclosed the above two fields and labels within a new box labeled Critical material properties o Enclosed the actual stress entry controls S0 S1 S2 S3 S4 within new boxes labeled Applied stresses NASFLA NASSIF Changes When OPS is not enabled the stress variations used to determine K values are assumed to vary linearly among user specified stress data pairs Previously the variations among stress data pairs were always represented by Hermite polynomials regardless of OPS being enabled or not NASFLA NASSIF NASCCS NASGLS Changes For crack cases CC04 CC07 and SC04 the crack case diagrams have been revised and clarified Crack cases DT01 DT02 DT03 The default interpolation type for these data table solutions has been changed from Spline to Linear Us
13. hich would either add or subtract cycles to the last step of the edited spectrum e For ID Q3LPI8AB1 the ultimate tensile strength was corrected to 205 ksi after verification e Stability issue when involving temperature dependent material properties specified in USRMTM The problem manifested itself by not generating any fatigue crack growth prediction for the specified interpolated temperature and at the applied stress level larger than and close to the threshold stress This release should resolve this problem that allows users to apply stress level very close to the threshold stress e The threshold values at c tip in the OUT2 file were all marked by x instead of showing their numerical values It was found this bug was related to the above stability bug fix where temperature effect was accounted for as a result of incorrectly computed threshold e Crack case SC17 For symmetric crack input W B 2 the geometry edit on the Crack Size Limits fields was incorrect For a symmetric crack only the a and c limits fields are shown while the geometry edit logic was referencing the c and cl limits fields requiring equal entries This check has been removed e User may receive an array overflow error message when selecting a second ID in the Compare Two IDs dialog e Incorrectly converted values for entered R values prevented the plotting of tabular material data e When saving plotted tabular material data to text file a GUI cra
14. hrough cracks at an offset hole in a plate under remote tension bending and pin bearing stress This model was developed by NRC Canada TC23 Additional Stress Intensity Factor Model Improvements also in NASSIF e CC08 and SC18 WF solutions for cracks at holes now allow application of in plane remote bending stresses S2 e Enhanced printing of stress gradient info including OPS and shakedown in OUT1 and STRESS CSV files as well as being viewable in the output window on the Computations tab e For TC15 the capability to plot the input stress gradient data was added Other New NASEFLA Features e Implemented ability to compare graphs of two material IDs user or NASGRO file on Material tab by clicking on the Compare two IDs button cpr Mak EE Material IDs Select ID 1 M2EA11AB1 from materials list 2024 T3 Clad Bare Sht L T LA HHA Select ID 2 M2EC31AB1 from materials list 2024 13511 Edr L T LA HHA Plot parameters Thickness and at least one R value are required Revalues 00 Thickness 0 2 Material to use for analysis optional ID 1 ID 2 e Implemented the Willenborg load interaction models for 3 D and 4 D cracks including the generalized Willenborg model the modified Willenborg model and Chang Willenborg model e Implemented the capability to handle situations where the structural responses stress gradients of a complex system at time in
15. ht function cases Excluded the applied peak stress from net section yield NSY check for weight function cases For 3 and 4 DOF crack cases the Cth value used in analysis option 0 initially is not allowed Changed Willenborg text labels for Shutoff Overload ratio and PhiO replacing term suggested with typical When plotting material fits separate independent access is now allowed for plotting Basic fits plotting Comparison fits and showing the References data for each material plotted via radio buttons on the Material GUI page On the Load Blocks tab the default block type has been changed from predefined block to manual input e Crack case CC08 SC18 TC13 OPS option will be automatically selected whenever crack stress definition is set to remote tension CC08 SC18 or tension bend TC13 e Internal routine to determine crack case 3 or 4 dimension status was corrected and appropriate GUI restrictions based on this status are now done correctly such as allowable load interaction models e An internal storage array associated with a grid was not expanded to a newer larger size which was needed when the associated grid itself was previously expanded This resulted in intermittent problems with the GUI e Changed the mechanism to handle flat load steps for the load blocks entered by Select file s containing long block s Before version 7 0 no check for flat load steps was pr
16. ifies the coding required for future changes as well as fixes occasional issues caused by the shared memory not creating properly Fixed an issue where modifying selection criteria on the Toughness Notes pages would not modify the displayed data to match the modified criteria or would not display data at all Resolved multiple issues where NASMAT would not properly plot material ID s when using the New Curvefit Plot button with only plot checkboxes selected b 1373 1383 1400 For ID Q3LP18AB1 the ultimate tensile strength was corrected to 205 ksi and the yield strength was changed to 180 ksi after verification b 1378 21 Resolved issues when saving or editing data in the user or NASA data files When editing or adding data material ID entries would occasional duplicate or be saved without capturing all of the changes b 1375 1382 Resolved issue where NASMAT would occasionally throw an error message when viewing da dN points on the Enter Examine Edit dialog b 1399 Fixed issue that caused plots to fail on occasion due to extraneous white spaces in the data file b 1389 Crack growth data for the following materials were added to the files and made available to the user ID M2EA11ABO1F amp M2EA11ABOIL 2024 T3 Recent Changes Documentation All Recent Changes lists have been reformatted separating them by NASGRO release version Multi level selection menus have been added for easy access to the individual
17. interpolation scheme among reference K solutions has been revised due to a strange SIF variation for a c near 1 0 for a constant surface crack length Crack case TC17 when changing the notch shape the geometry grid entries common to both configurations if entered will be retained Crack case TC18 when changing the embedded hole shape rows in the geometry grid labeled Hole half width d Notch tip radios r for straight edge hole and Semi major axis el Semi minor axis e2 for elliptical hole will no longer be retained since these values are unique to only one embedded hole shape When using separate tension compression data via files plotting this data could result in a file missing error due to an incorrect internal filename reference Crack case TC18 solution validity limits have been corrected both in the displayed crack case diagram and the geometry edit checking routine straight edge slot upper limit of d r B corrected from 0 9 to 0 75 elliptical hole upper limit of e1 B corrected from 0 9 to 0 75 Crack case TC18 solution validity limits have been corrected both in the displayed crack case diagram and the geometry edit checking routine expression 0 lt B W lt 0 75 corrected to 0 lt B D 2 W lt 0 75 Crack case TC13 When the input values for crack dimension are exactly at the limits for solution accuracy validity a computation core error was issued An additiona
18. k case TC12 This has been fixed e Crack case TC18 Very small point spacing at the notch tip causing a large number of points during iteration resulted in an extremely long analysis completion time Revisions to the OPS routines have corrected this issue e Crack case SC10 corrected an error that was preventing the applied stress SO from being echoed in the output file when computing SIF values e Crack Case TC11 Several uninitialized variables caused differing results between batch mode processing and single input file run mode for the same set of input values This has been corrected e Crack case TC13 Include residual stress checkbox inadvertently remained on screen when stress distrubution selection set to Tension bend NASFLA NASSIF Fixes e Crack case SC17 The interpolation scheme among reference K solutions has been revised due to a strange SIF variation near a c 1 for a fixed surface crack length e Crack case SC18 the interpolation scheme among reference K solutions has been revised due to a strange SIF variation for crack shape aspect ratio around 1 0 e Crack case SC19 The interpolation scheme among reference K solutions has been revised due to a strange SIF variation for a c near 1 0 for a fix crack depth e Crack case CC08 The interpolation scheme among reference K solutions has been revised due to a strange SIF variation for a c near 1 0 for a constant surface crack length 16 Crack case CC10 The
19. l tolerance has been implemented to allow for such a numerical accuracy problem A screen layout issue caused GUI input grids that needed exactly one scrollbar either a vertical or horizontal to also have a second unneeded one Also in NASCCS amp NASGLS Validation of maximum allowed value for crack size c was incorrect preventing certain inputs from running Corrected a problem with Optimum Point Spacing for residual stress Crack case CC14 corrected a typo in the routine that checks the solution validity limits for the elliptical hole configuration which prevented some analyses from running 17 e 2D bivariant stress input files were not being read converted properly during plotting Plot Stresses button preventing stress plotting and incorrectly displaying the error message Number of points in x direction must be an integer e Corrected an Nan error that resulted from incorrect temperature interpolation e The option to save plots in PNG format was inadvertently lost e When saving plotfile data to external file the chosen file extension was not added to the filename if that filename contained a period e Crack case TC11 computational core assumed the incorrect symmetry option for non symmetric loading during calculations e Crack cases CC14 SC27 incorrect data written to batchfile prevented some analyses from running e Corrected error causing incomplete computations related to Optimum Point Spacing
20. loading a NASFLA input file for which no material data had been saved NASFLA GUI would crash during the selection of a temperature related material ID if the Cancel button was clicked during the selection of the form orientation environment set to be used in calculations When using predefined block data on the Load Blocks tab the data displayeed in the grid was not being properly updated for BLOCKS or BLOCKT databases when a material ID selection was changed between a temperature related material ID and a non temperature related material ID Basic and Comparison curvefits and References for temperature based materials could not be plotted or viewed If more than four temperature dependent load blocks were used in an analysis varying output results occurred 12 Crack case CC09 crash of computational core occurred due to incorrect memory usage A batchfile error prevented analyses from running in elastic plastic mode Some R values on material curvefit plots were incorrectly represented in exponential notation Incorrect value shown in the plot legend REF column when plotting the Basic fit for material ID M7GJ11ABO01 for data ID M7GJ11ABO1J1 Crack case SC27 an error in writing crack size data to batchfile caused incorrect results The following GUI radioboxes were not prompting the user to resave input when their settings were changed Cth value used in analysis Temperature interpolation type Strip yield computational
21. ns of TC18 A wide range of geometry parameters is allowed Stresses can be applied as remote tension in plane bending or un cracked crack plane stresses cc14 cc14 Bh O Taklit Hd C h zo C27 S pt 0s 3 0 75 sttttttttt a 0 25 lt s 1 lt 2 Fral 02s lt 5 Je 02 lt 38 1 W c e CC15 Corner Crack at Offset Hole in Plate with Broken Ligament e SC28 Surface Crack at Offset Hole in Plate with Broken Ligament o These univariant weight function SIF solution are for corner and surface cracks at a hole in a plate with one of the net sections completely broken through and are extensions of TC19 o These crack cases can be used to describe a continuing damage scenario after the short ligament in the TC13 crack case is broken through and a corner or surface crack initiates at the opposite side of the hole The broken ligament is represented by two parallel edge surfaces with an infinitesimal gap Stresses can be applied as remote tension in plane bending or un cracked crack plane stresses CC15 C28 s Dey s er r 0 lt 8 lt 24 CECE PEET 4 tttttt ttt 0 0 lt 2B lt 0 So gt D o lt B D 2 lt 075 o lt BEDIZ s 0 75 rer W B D 2 _ __ lt 099 W B Di2 nE e Sof firir IT Sof pir ITT a Soa Sprett 2s 098 sp 25095 gt B D 2 je B D 2 lt 8 Ji 24 ft hae C c e TC23 Unequal Diametrical Through Cracks at Offset Hole in Plate also in NASCCS o This SIF solution is for two unequal t
22. ons if the iteration does not converge Additions NASFLA amp NASSIF Made the following modifications to OPS univariant stress data plotting o Added User Data to the OPS plot as well as its Linear interpolation curve for comparison purposes with the OPS generated data points and the OPS generated Hermite interpolation curve o Removed control knots from the OPS plots These are internal points used in the data generation routines and by themselves are not relevant to the plot itself Additions NASFLA NASSIF NASCCS amp NASGLS Upon completion of an analysis the GUI will now automatically display the Output Summary information in the display window on the Computations tab Previously the user was required to manually click the View Output Summary button for this information to be displayed Added a new Release notes button on the main NASGRO GUI opening screen and a new individual GUI Help menu item NASGRO release notes which accesses the distributed PDF file listing all features of the new NASGRO release For very short anaysis runs it was possible for the newly saved input file timestamp to be slightly older than its resulting outlfile timestamp causing a warning message to be issued in error at the end of the run when the output summary data is automatically displayed in the output viewing window NASFLA Changes Included the net section stress caused by limit stress in net section yield NSY check for weig
23. sh occurred preventing the saved log values in the file from being converted to anti log values e Crack case SC18 output showed inconsistent a c and a c values as well as NaN not a number printed at the final result summary section for DKth and DK Two errors were identified and resolved One was from the SC18 fracture mechanics software module which could affect the computed reference solution through dynamic K table interpolation when NASFLA GUI was utilized The other resulted from incorrect output designation such that inconsistent values were printed NASSIF Fixes e Crack case CC11 The upper validity limit for crack shape aspect ratio a c was incorrectly implemented The fix implemented the correct upper bound ratio i e a c 40 14 An internal variable became un uninitialized causing program crash A memory leak caused by allocated memory which was not correctly de allocated has been corrected Some uninitialized variables used in batch mode for multiple input files caused incorrect results This has been corrected An un initialized variable resulted in unnecessary memory allocation leading to an unable to allocate message when running multiple input files in batch mode This has been corrected Crack case SC17 internal sub program names were isolated and renamed to resolve a problem of slightly different results due to possible reuse when running multiple input files Crack case SC04 An invalid program str
24. stants t and f of a cyclic loading are different This new feature is available on the Geometry GUI screen for the following weight function solutions o Univariant WF solutions 12 crack cases TC11 TC12 TC13 TC17 TC18 TC19 CC08 CC11 SC17 SC18 EC02 EC05 o Bivariant WF solutions 5 crack cases CC09 CC10 CC12 SC19 EC04 Crack plane stress definition from C Tension bend User input of stress distributions Shakedown choice 10C2C3C 4 None C Automatic Full cyclic V Optimize point spacing M Include residual stress IV Input stresses from file I Plot stresses i 5 pen stress quantity I Tens Comp stress gradients S0 C Cy os g IV tl t2 stress gradients J ot stress gradient att gt p p ot stress gradient at t gt a A e A Gj g x x 2 Stress gradients 14 444 tO S Applied stresses Ss F S0 t where o 0 ath o 0 att Fatigue spectrum New fields in GUI and input file are now available for the user to supply information describing the problem being analyzed This feature is accessible from the Output Options GUI screen See below Implemented the capability for computing the number of cycles to user specified intermediate cracks sizes This feature is accessible from the Output Options GUI screen AS ck ha IIE File Options Tools Help ey Geometry ESE
25. ucture resulted in a NaN not a number error Crack case SC04 An uninitialized variable resulted in an inconsistent echo of user provided stress values in the output Crack case TC18 uninitialized variables in internal static libraries caused different output results Crack case TC11 An extraneous character written to the output of the SIF table has been corrected removed Crack case EC04 Unnecessary memory allocation during computations in batch mode caused early termination due to unable to allocate memory error This has been corrected Crack case CCO9 error in OPS routines has been corrected Crack case CC10 Corrected the problem of INF meaning infinite value written to the output due to an incorrect computed crack depth ratio Crack case CC12 Incorrect program calls to crack transition routines caused program crash Crack case CC11 Corrected inconsistent results output due to internal library issues 15 e Crack case CC08 An uninitialized variable caused the following error to be erroneously issued Crack size exceeds bounds for solution accuracy e A memory leak caused by internal library was identified and corrected e Crack case TC17 Very small point spacing caused accumulation of numerical inaccuracies Improvement in the pre integration routine has corrected this issue e Crack case TC15 A problem with the index searching algorithm caused inconsistent SIF results with crac
26. ues with the User and NASA toughness check boxes on the Toughness Notes page Checkboxes may only search one file at a time and only display Edit Enter data when the user has permission to edit that file On the Toughness Notes page some searches were listing entries but not displaying them when Show Selected Data or Enter Edit Data were chosen This has been corrected to properly show all data that matches the filter criteria On the Toughness notes pages selecting some specimen types were displaying a different number of matches than shown when viewing the matches on the Enter Edit or Show Selected Data page This has been corrected and the number of specimen types that can be used to filter the results expanded Pressing the Enter Edit Data button on the Toughness Notes page would bring up a superfluous pop up stating Please Enter a data ID The pop up has been removed The Toughness Notes page was unable to open the user toughness data file This has been corrected The Toughness Notes pages would display erroneous numbers when selecting a filter criteria when no ID had been selected This has been changed to properly display 0 NASMAT s utilization of the Windows Registry to store some user specific data has been changed to use an initialization file instead NASMAT no longer utilizes the Registry Removed NASMAT s reliance on shared memory when executing nasmat dll and replaced it with a file pipe This change simpl
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