NASGRO v6.1 Release Notes
Contents
1. also in NASGLS Corrected all column headers in CSV files for both the computed output out2file and compounding data out3file On the Material Tab reworked the logic to consistently display the valid Data Formats for all combinations of Crack Growth Models and Data Sources User is now prompted to resave input file for the following functions of the Load Blocks Manual input grid Erase entire table Paste from clipboard Fill grid from file Keac chk checkbox was not being created in the first column of newly added rows in the Load Blocks Manual input grid for the following functions Insert a row Delete this row and Delete empty rows The delete functions remove rows then insert new rows at the bottom of the grid Load Blocks Manual input grid function Fill grid from file was incorrectly saving value delimiters to grid cells Disabled the Save input to User material file after computations checkbox on Material tab to prevent program crash that occurs when attempting to save new data to the user material file for 2D Walker interpolation table BLOCKS BLOCKT file spectrum grid data may now be saved to file Buttons for Show frequently used materials list and Enter ID code directly on the Material Tab were not shown for some combinations of Crack Growth Model and Data Source selections Some screen controls were out of place for Material Tab selections of Crack growth model Constant Closure Data source New data and Dat2. for all R lt 2 was judged to be excessively conservative The new algorithm employs the Newman closure equations Equations 2 3 through 2 7 in the NASGRO Reference Manual for all negative R values based on further guidance from Dr J C Newman Jr The new NASFLA algorithm is consistent with the algorithm that has always been employed for similar purposes in NASMAT This change will not affect crack growth calculations in which R gt 2 For crack growth calculations in which R lt 2 the new algorithm will predict longer lifetimes Crack case TC16 Implemented damping effect and non zero biaxial load ratio for Chen Schijve model also in NASSIF The Schedule title will now be correctly loaded if it exists in the file used to load the Schedule assembly grid on the Build Schedule tab Crack case SC08 Changed checkbox label from Perform bolt preload analysis to Perform bolted joint analysis also in NASSIF amp NASCCS Crack case CC12 Changed geometry limits from 50d to 10d Min W 8 10d also in NASSIF amp NASCCS Crack case TC16 Updated Appendix C of the manual with modifications relating to the broken stiffener also in NASSIF amp NASCCS Redesigned the formats of the column headers in out2 and out3 files also in NASSIF NASCCS amp NASGLS Removed Max min warning for spectrum editing cycle counting options Modified rainflow and Downing Algorithm I Increased size of the manual input spectrum grid on the Load
3. Blocks tab from 200 to 400 rows Merged out3a and out3c files which store compounding factors during crack propagation into a single file out3 When material data and output out2file out3file data is plotted these plots will now be rendered using all calculated points connected with lines only no symbols Previously plots were represented by symbols only without connecting lines and displayed approximately 100 points each to optimize readability Increased block repetition limit from 9 999 to 99 999 in Distinct block case repetition table on build Schedule tab Removed 1D table data format choice from the following two combinations of crack growth model data source choices Non interaction NASGRO material file and Constant Closure NASGRO material file since the 1D table data contained in the NASGRO material files are DKeff data which is usable only by the Stip Yield model NASFLA Changes Materials Material selection lists have been modified to display both US and metric units for entries containing strength and temperature information in their descriptions This applies only when choosing NASGRO equation constants as the data format and either NASGRO material file or NASGRO material file multiple temperatures as the data source Material files affected NASMFC NASMTC NASMFM NASMTM The following fixes and changes were made to the NASFLA materials files HY 140 Steel ID E2DA12AB1 Kle amp K1c values
4. compounding table e During transition the compounding data specified for the original geometry are passed onto the post transition geometry e Compounding factors are saved during crack propagation and can be plotted in post processing via the select details to plot window on the Computations screen e The new compounding features are documented in Appendix C of the v6 1 user s manual Section C10 page C 102 e The Geom Tables GUI screen show below is an example of how the GUI would appear for entering 1 D compounding tables for the c tip for crack case CC02 GINASFLA Crack Growth Analysis 5 x File Options Tools Help KB Geometry Pl GeomTables Material J Load Blocks BulldSchedule F YOutputOptions 47 Computations r Show tables for C atip ctip V Do compounding for 0 MV Do compounding for 1 MV Do compounding for 3 Right click set no of tables Right click set no of tables Right click set no of tables ae display and or a an display and or 3 me display and or c D1 c D1 i c D1 l i z z D1 fio D1 fio D1 f o Interpolation Piecewise linear Interpolation Piecewise linear Interpolation Piecewise linear Change interpolation type Change interpolation type Change interpolation type A new set of additional optional failure criteria were developed for crack cases
5. using the right click command Import export gt Fill grid from file Post processing CSV output file was not being created for SIF compounding data when CSV files were requested by the user in certain instances A problem caused by stress file names starting with the letter n has been corrected and the restriction removed also in NASSIF 5 e User specified fracture toughness was not accounted for by the NASFLA core for fatigue crack growth computation e When plotting user provided stress input data the blue line used to illustrate the behavior of these data points showed some discontinuous cut offs at the minimum of the residual stress gradient which while not an error was misleading Plotting has been adjusted to account for the OPS point spacing in addition to the user provided data points for generating the blue line e Crack case TC11 when applying FAD analysis the computation was terminated unexpectedly due to an inconsistent crack tip designation being assigned also in NASSIF e Threshold Alpha fields on Material tab was not being correctly re shown on screen after certain GUI changes causing a processing error e GUI crashed when trying to display the computed results due to a missing pound sign at the beginning of non data lines in the OUT2 file e Modified the Willenborg set of computational engines now enforcing immediate termination of crack growth analysis when the net section stress exceeds the yiel
6. were changed to 180 ksiVin 6255 MPa mm and 130 ksivin 4517 MPaVmm respectively in the material files NASMFC amp NASMFM 2219 T87 320F ID M2IFB1LA4 Properties in multi temperature material files NASMTC amp NASMTM made to match mono temperature data Inconel 600 75F amp 1000F ID Q3ABI0AB1 amp Q3ABI0AA18 Properties in multi temperature material files NASMTC amp NASMTM made to match mono temperature data Inconel 718 1000F ID Q3LB23AA18 Properties in multi temperature material files NASMTC amp NASMTM made to match mono temperature data NASGRO equation constants for the following alloys were added to the materials files a M2TAI3AB1 2195 T8MA b E4EB28AB1 E4EB29AB1 amp E4EB29AC1 Pyrowear c L6AB28ABI1 Jethane M152 Strengths were changed based on a scrutiny of the source material of the following Titanium alloys a P6AAI16AB1 b P6ABI6AB1 Curve fit constants for the following ELI Titanium EB weld alloys were removed a P3EMD2AB1 b P3EMD2LA4 c P3EMD8AB1 d P3EMD8LA4 The following 7010 Aluminum alloy was removed since basic da dN data for it was lacking in the NASMAT files a M7DC12AB1 An erroneous CP for Commercial Purity was removed from the description for the following Titanium weld alloys a P3EDB2AA1 b P3EDB2AB1 NASFLA Fixes Changed output formats to display large Kc values properly Modified code to make fatigue spectrum with zero cycle steps generate
7. August 3 2010 NASGRO v6 1 Release Notes NASFLA Additions and Changes e Crack case TC16 through crack in a curved stiffened panel was enhanced to account for a 2 bay crack with a broken stiffener for both the Swift and Chen Schijve bulge factor models TC16 now also allows the use of the Swift bulge factor for 1 bay cracks Also in NASSIF and NASCCS e A capability to input separate stress gradients for tension and compression loads was implemented for the following weight function cases e Univariant CC08 CC11 SC17 SC18 TC11 TC12 TC13 EC02 and ECO5 e Bivariant CC09 CC10 CC12 SC19 and EC04 This new feature is documented in Appendix C of the v6 1 user s manual Section C9 1B page C 89 and is illustrated in the figure below t Geometry and loading Stress gradients e The compounding features in both NASFLA and NASSIF have been revamped and enhanced and now provide much more flexibility and options e Compounding capabilities are now available for all through cracks all corner cracks and all 1 D 2 D surface cracks 44 crack cases in total and can be activated by checking a box on the Geometry GUI screen for each crack case Compounding tables can then be entered via the Geom Tables GUI screen e Implemented capability to specify multiple compounding tables for each stress component SO S1 etc e A different user s normalizing dimension and interpolation scheme can be specified for each
8. SC17 EC02 EC05 CC11 TC11 TC12 and TC15 These new failure criteria include plastic limit load a failure assessment diagram FAD according to FITNET Option 1 and FITNET Option 3 and the Newman Two Parameter Fracture Criterion TPFC Documentation for these new failure criteria is provided in the new Appendix X to the v6 1 manual The shakedown option was added to crack cases TC11 TC12 and SC18 An option was added on the Material screen for the NASGRO equation that allows the user to change Threshold Alpha the constraint factor in the Newman crack opening function used for fatigue threshold calculations The default for the Threshold Alpha is 2 0 A label is printed in the output files exe or dll to indicate if the results are generated by running the executable or the DLL Converted the step interpolation of the Newman crack closure function at both the near threshold and Paris regions to instead perform piecewise linear interpolation avoiding the small step discontinuities in the results when the stress ratio R is continuously varied Significantly increased speed of net section yield NSY analysis for weight function cases The algorithm used to calculate the crack opening function f and the effective stress range ratio U 1 f 1 R in the NASGRO crack growth equation has been modified for R ratios algebraically smaller than R 2 The algorithm used previously in NASFLA which set AR and U R equal to f 2 and U 2
9. a format 2D table diff dadN set for each R Narrowed the list of allowable combinations of Crack Growth Model Data source and Data Format on the Material Tab Material Tab now shows proper screen controls data source choices data format choices for a given crack growth model selection Incorrect material file was loaded for some changes to selections of crack growth model data source and data format Fixed Material selection button now correctly redisplays changes for all Crack Growth Models Crack cases TCO5 SC03 Compounding tables for stress quantity S4 were not properly loaded from input file Corrected problems with displaying crack growth percentages during execution in GUI lower status bar A warning will now be issued for a transition from CC03 TC04 if after transition D W gt 0 5 Fixed the empty out3 files encountered when choosing to not continue compounding after the transition by adding statements to flush out the contents of the buffer Variables related to the threshold fanning factor Cth were positively initialized in four of the computational engines to prevent inadvertent elevation post transition of the threshold An error with the preload calculations in crack case SC08 was corrected Crack case TC14 corrected error in geometry edits for c W requirement which erroneously prevented certain analyses from being run Removed references to distance and units from weight function stress plot diagram labels since thes
10. ata points were displayed when the curve fit constants were changed from those originally obtained through the least squares process Errors were fixed related to selection of IDs to be used for fitting in the post sort phase of the display Problems that arose when multiple files were invoked and loaded for the same R value were fixed Display of all data is now possible when choices of forty or more IDs are made on the Data Identification page 10 e Errant points in the da dN materials files were removed for the following 7150 Aluminum alloys M7PF11ABO1A1 and M7PF11AB01B3 e Inconsistencies in values when using the Enter Edit Constants and the Comparison Fit buttons on Curvefit Plot tab have been corrected e No plot was generated through the proper use of the Comparison Fit button on the Curvefit Plot tab Fixed NASFORM Changes amp Fixes e Improved communication between the GUI and the DLL by making the GUI wait for the Fortran to finish before displaying the results e Fixed a problem of erroneous erasure of the stress data when loading from a file if the US UK system of units was selected at the beginning e A recently introduced file name mismatch which was preventing access to the user manual from the GUI was rectified 11
11. ay next to the Calculate Kc button to red and the button itself now changes color to emphasize a necessary step that must be taken before proceeding further On the Curvefit Plot page the minimum and maximum values entered by the user are retained for the duration of the session for the y axis le 10 and 001 are set as the default values Allowed the files selected for loading data into the da dN versus Delta K grid to be displayed in alphabetical order Positioned the plots to be displayed in the center of the screen Modified the plot default values to change according to the chosen system of units and froze the source units option after a selection is made disallowing any further change to the system of units for the duration of the session On Enter da dN Delta K tab when selecting Data Source as File FTA format the Browse button s file selector will now start with default file type DAT dat for easier data file selection Previously All files was the default type Temporarily disabled Plot Fit button on Curvefit Plot tab if Kc needs to be recalculated due to a change to any of the following values K1c YS Ak Bk Thk NASMAT Fixes Fixed error with plotting of all da dN versus Delta K data removing display of spurious warning Wrote code to filter out invalid characters such as alphabets in a numeric field and set most of the Text Controls as Read Only Fixed plotting problem wherein fit but not d
12. correct results Crack case SC02 Corrected equivalent stresses calculation 4 Fixed occasions of GUI incorrectly being set to manual material mode in some cases Corrected the following errors for spectrum visualization o There was no statistical analysis output for S3 stress in some instances o X axis labels for MinMax plots were overlapping for large cycle values Labels will now incorporate k for values greater than 10 000 10k o Internal error caused a crash during generation of stress level histograms o Certain GUI controls incorrectly caused user to be prompted to resave input file which is not needed since visualization does not change input values When changing Material properties Data source on the Material tab the block selection radio box For this block was being incorrectly set to the first option Crack case CC08 Stand alone executables generated by two different compilers computed different FCG lives when cyclic shakedown was used This problem was caused by an uninitialized variable in the cyclic shakedown routine GUI users should not observe this bug Crack case EC04 o Inconsistent results between v6 01f and v6 10b were reported The output showed early termination after transitioning to a CCO9 crack and during the next transition to a TC12 crack which was caused by an inconsistent internal variable assignment o Incorrect transition to a CCO9 crack was reported Post transition crack sizes were inc
13. d strength This eliminates a lag between when the condition occurs and when the analysis is brought to a halt an error which existed previously when single cycle steps were invoked e When changing the interpolation type for each SIF Compounding data table the dialog window selection was incorrectly defaulted to Piecewise Linear Now this will be set to whatever is shown on screen which initially is Piecewise Linear but may be any type if a previous selection has been made e Incorrect GUI prompts caused post processing CSV file for out2data to not be loaded into spreadsheet program for cases with no SIF compounding and may also cause a program crash e SIF Compounding data interpolation type is now set properly when loading older 6 0 input files e Modified the required stress quantity values under Generate acceptance vibration block to make the cycle calculations conform to the underlying analysis NASGRO Manual Appendix H The GUI now asks for a single value of Max peak stress for each of the stress quantities instead of asking for values at tl and t2 since the analysis assumes fully reversed cycles R 1 also in NASCCS e On the Load Blocks tab the Set all scale factors to those of block 1 button now properly copies the block 1 scale factor to all other defined blocks when using the button also in NASCCS The following NASFLA fixes also pertain to NASSIF and NASCCS e Crack case TCOS o Excluded stress SO in net s
14. e values are non dimensional When rechecking Do compounding for Sn checkbox the GUI will now remember and restore the previous number of tables defined for that stress quantity Previously if more than one SIF Comp table was defined the Do compounding checkbox was unchecked then rechecked number of defined tables would be set to a default value of 1 User is now prompted to resave input file when changing SIF Compounding GUI settings Crack case TC16 Removed incorrect zero default value for Stiffener spacing L Crack case CC02 Modified to issue a warning to the user about the inaccuracy of the solution for stress quantity S1 when certain geometric bounds were exceeded also in NASGLS Crack case TC09 Modified to issue a warning to the user about the inaccuracy of the solution for stress quantities S1 and S2 when compared with crack case TCO3 also in NASGLS Crack case TC10 GUI was incorrectly calculating the value of R by using D t The correct expression for R is D t 2 Crack case TC16 also in NASGLS o Corrected loading of older input files created before version 6 1 beta when Damping factor F was not yet available for the Chen Schijve bulge factor model o Due to problems in 6 1 beta if a 6 1 beta input file is attempted to be loaded the user will be prompted to re enter the geometry input and resave the input A GUI crash that occurred whenever raw plot data is saved to a text file was fixed also in NASGLS Running an i
15. ection stress calculation if user specified D B is non zero o Added GUI input verification to prevent the combination of SO scale factor and non zero D B o Updated crack case bitmap indicating D B must be set to zero for tension loading e Crack case TC16 Allows zero value for Damping ratio F 6 Crack case ECO5 Corrected error in geometry check which disallowed valid input Fixed erroneous display of available curve fits of tabular stress intensity factor data by converting the vectors of fit information into allocatable arrays Added a radio box to certain crack cases to correct a DLL processing issue where the value of Kcr was incorrectly set to zero in the post transition phase Crack case SSO5 Updated all GUIs to consistently use label L for the Span dimension Stress data from very old input files are now being loaded correctly Crack case CC01 Added the existing FORTRAN restriction W to the GUI Previously the GUI allowed t gt W which prevented the creation of output also in NASGLS Crack case SC17 Corrected displayed upper limit for a t ratio to be 0 9 also in NASGLS Corrected the GUI status line to properly show all relevant crack tip growth percentages during execution In addition Model has been added to the status line to convey both the initial as well as any post transitional model s also in NASGLS Corrected the column headings for the S4 stress quantity which is present in crack cases TCOS5 and SCO3
16. nput file via the command line no longer erroneously prompts the user to resave the input file prior to the run also in NASGLS Corrected a problem in batch processing mode which halted the automated process when any input file run returned an error also in NASGLS Crack case TC15 Inconsistent results with crack case TC12 for a plate of uniform thickness The problem originated from incorrect dual indexing for point coordinates used separately to describe stress and thickness variations as well as a typo in one of the terms to derive pre integration weight function solutions NASSIF Changes amp Fixes Re arranged the tabular output for two dimensional flaws so that rows associated with a fixed value of a c are clustered together Changed output formats to display SIF correction factors properly Crack case SS02 Fixed error caused by misaligned stress input value in batch file Crack case TC08 Newline character from input file incorrectly loaded to crack sizes table causing error during computations Crack case TC11 Internal error caused no crack size data to be written to the batch file Crack case SC17 enabled proper upper limit for a c to 8 0 Corrected program crash if D W gt 0 5 for crack case TC04 Corrected for all crack cases the flat lining of the plots of tabular correction factor results GUI program crash occurred when user attempted to plot an external stress file in the Alternative 2D stress input format NASCCS Fi
17. onsistent when compared with those from v6 01f leading to different fatigue crack growth lifes The problem resulted from recent program re structuring such that the crack model after transition was specified incorrectly Crack case SC08 Modified the segment performing bolted joint analysis correcting certain expressions and introducing a variable L threaded grip length to be entered by the user to enable the stiffness of the threaded bolt to be accurately calculated Crack case SC19 Computation terminated during a transition to a TC12 crack due to incorrect post transition specification of the parameter designating the number of crack tip degrees of freedom Crack cases CC11 EC02 EC05 SC17 TC11 TC12 TC15 When loading an older input file containing the Bypass net section stress checks flag this flag was not being properly converted to the new Failure criteria setting Net section stress on the Material tab causing different output results When saving material plot data to text file the header line containing the material description has been restored CSV file containing computed compounding data is now being properly created for all corner and surface crack cases Prevented crash when attempting to load a table from file when that file is larger than the table File separators were being erroneously loaded as trailing characters in the first column of the Distinct block case repetition table on the Build Schedule tab when
18. xes GUI fixed such that it no longer crashes when selecting SI units Crack case DTO1 GUI no longer crashes when attempting to plot table data NASGLS Fixes Changed output formats to display sustained stresses and time with three decimal places Material properties are now correctly loaded when material selection is SI Units NASMAT Additions A console application using the shared memory technique was implemented in NASMAT to handle inter process communication to prevent the GUI from crashing in the event of a crash of the core program Informational notes were added regarding units in the Enter da dN Delta K and Enter a vs N pages NASMAT now has the ability to deal with the possibility of user source data being entered in SI units with length in meters instead of in millimeters The Crack Tip default was set to both tips if user chooses the Variable Kmax and R option for K Control Mode Seven new sets of material data fatigue crack growth rate data were added to the NASMAT database The new material names and corresponding NASMAT database IDs are listed below 4340 Steel C4DF22AB01B ACOIA and B D6AC Steel E1DA22ABO01A and B and ACOIA AerMet Steel EINBI8ABOIA and 19ABOIA Pyrowear Steel E4EB29AB01A 2198 T8 Aluminum M2RA11AB01A and 12ABO1A 7075 T7351 Aluminum M7HH12AB01H 7085 T7452 Aluminum M7WB21AB01A C D 22ABOIA C D and 2SABOLA NASMAT Changes Changed the static text displ
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