Progressive Failure Analysis (PFA) Static Un
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1. Note The intention here is to subject the coupon to uniform stresses and remove any possible free body motion in the FE Model Boundary Condition Y direction Similarly select all nodes in the whole model From the Boundary Conditions panel select the Boundary Z item in the type list and click the Apply to Selected Nodes Boundary Condition Z direction Close the Boundary Conditions panel by toggling the menu item under the Constraints submenu under Setup menu Unselect the selected nodes by clicking on Select None button under Node Selection sub panel within Nodes panel Close the Nodes panel by clicking on the Nodes icon 8 next to the model view window The FE Model setup is now complete We can now proceed to the Progressive Failure Analysis Progressive Failure Analysis PFA Static Un notched Section 2 1 16 Coupon Step by Step Tutorials Analysis Type and Settings 55 Be sure that the Analysis Mode to Static Eb 3 Input E Analysis Mode Parameters z Advanced Settings E Sover mos F 56 Be sure that the Solver is set to MHOST 57 Double click on Analysis Mode Parameters node under Analysis Mode or right click it and select Edit 58 Make sure the Number of Nodes Elements Allowed to Damage is set to 24 59 Make sure the Number of Nodes Elements Allowed to Fracture is set to 4 Note The Number of Nodes Elements Allowed to Damage is set to 10 of the total nodes while the Number of Nodes El2. cod Delete Fj Analysis Note the present tutorial is for PFA static analysis in dry condition only mechanical properties are considered and other hygral thermal electrical properties can be ignored You should see the following after adding the Mechanical option Fiber 1 El CARB Q Description None Temperature 4 E11 0 men EN 0 IbFifin 2 G12 0 Ibf in 2 G23 0 lbf in 2 NULZ 0 AUZ 0 S117 0 Ibffin 2 410 0 Ibt in 2 Note Fiber properties are assumed to be transversely isotropic Double click on a single entry shown in red in the Figure above to edit the value Note You may right click on the node and select Edit from the popup menu To edit all the category values together in a table format you may right click on the category such as Modulus and select Edit to modify the values in table format Edit the values to match the Figure below Progressive Failure Analysis PFA Static Un notched Section 2 1 6 Coupon Step by Step Tutorials S Fiber 1 SOR O Description None 2 Temperature 7 000000E 01 F ot 9 Mechanical E11 3 139000407 Ibf in 2 E22 2 068000 06 lbf fin 2 G12 2 301000E 406 Ibf in 2 G23 7 07 7000E 405 lbf in 2 NUIZ 2 88 1000E 01 NLU23 4 601000E 01 SLIT 5 346000E 405 Ibf in 2 S11C 3 957000E 405 lbf in 2 CARB Fiber Material properties Adding a Matrix Material 12 Right click on the Matrix node
3. Analysis PFA Static Un notched Section 2 1 20 Coupon Step by Step Tutorials Results Mesh Now we will look at the 3D model deformation and results 74 Double click on the Mesh node under Analysis Results node in the tree to expand the tree node 75 Right click Mesh node and choose View 76 Forward the iteration counter by scrolling the bottom slider to the far right or by clicking on the last iteration icon Pl below M iteration 1 FORCE X a4 3 068E 03 PEKAS al iterations x 77 Rewind the model to the first iteration by clicking the button or dragging the slider at the bottom back to the beginning 78 The Mesh node under Analysis Results node will also show available properties to view under the Mesh node as shown below which we will examine in the next sections 2 Mesh E Stress a3 Ply Stress a3 Ply Strain 4 Displacement Damage 79 Double click on Damage node under the Mesh node to view the node damages You may click on Damage icon B located to the left of the model view window Note Another option will be to press the space bar on the model view window to show the popup menu and choose Damage from the Results menu to view the node element damages Note By default All Damages item is selected to show every damage criteria that has occurred in the model at the current iteration During the initial loading no damage has occurred yet until the model reaches iteration 5 80 Drag the slider to iter
4. Open Project Progressive Failure Analysis PFA Static Un notched Section 2 1 3 Coupon Step by Step Tutorials Note GENOA recognizes the filename extension of dat as a GENOA format and automatically reads the file without any translation G Structures Libraries Se Project Library Ef Tutorials i Fatigue a Fracture H Importing Static a ee IPFA Static Flat Coupon H ASTM H Material Library pen Project Rename Import into Current Pre No Project Import into Other Direc Export to Project AP Delete Mesh View and Setup 4 Right click on the Mesh node in the tree under Input node and select Edit You may double click on the node to view and edit it You should see the FE model as shown below Imported FE Model made of 4 node shell elements Use the Left mouse button for rotation of the model Use the Right mouse button for translation of the model Use the Middle mouse button for zooming in and out You can click both left and right button and press forward or back arrow keys on the keyboard Roll the mouse wheel for fast zoom in and out Adding a Fiber Material 5 Right click on the Fiber node under the Materials tree node A Fiber material will be added to the fiber list Progressive Failure Analysis PFA Static Un notched Section 2 1 4 Coupon Step by Step Tutorials 5 ry Materials 0 a Hotel 1 SPO Bene All Items From Library a ynmeY Com 6 R
5. un Temperature 7 00000E 01 F Y A A Mechanical E 0 Ibfflin 2 ST 0 bff in 2 SC Obbfflin 2 SS 0 Ibf in 2 Note Matrix properties are assumed to be isotropic 17 Double click on a single entry shown in red in the Figure above to edit the value Note You may right click on the node and select Edit from the popup menu To edit all the category values together in a table format you may right click on the category such as Modulus and select Edit to modify the values in table format 18 Edit the values to match the Figure below Progressive Failure Analysis PFA Static Un notched Section 2 1 8 Coupon Step by Step Tutorials FHES Matrix 1 3 EPOX 0 Description None l Temperature Mechanical E 6 816000E 05 lbf in 2 NU 3 400000E 01 ST 1 450000E 04 Ibf in 2 SC 4 713000E 04 bbf in 2 SS 3 404000E 04 Ibf in 2 EPOX Matrix Material properties Adding a Laminate Laminates show all the laminate information in the model including the laminate sequence the use temperature orientation angles material type and thickness of each ply Since the material properties are entered at constituent level fiber and matrix the laminate definition contains both ply definition to identify the mixture content of fiber matrix and void as well as lamination stacking sequence and ply thickness Note Ply 1 is at the bottom and as the ply number increases it is stacked along the positiv
6. 055 Set Fiber Matrix CARB EPOX 70 0 0055 0 57 0 02 Fiber Matrix CARB EPOX 70 0 0055 0 57 0 02 29 Make sure all of the plies are assigned FailCrit_1 in the Failure column Fiber Volume Void Volume Pra Fraction Fraction 0 57 0 02 FailCrit_1 7 s 0 57 0 02 FailCrit_1 Material Type Fiber Matrix Temperature Thickness m Failure Strain Limit 30 Save the project by selecting Save option under Project menu or press Control S which you may be prompted to save it in another location since the current project is in a temporary directory This will ensure that no work is lost Laminate Assignments We will now associate the finite element mesh with laminate created above 31 Right click on the Mesh node and select Edit 32 Click on the Laminates Assignment icon on the left toolbar Note You can also double click on Laminate Assignment node under Mesh node in the tree LENUA Wednesday February 1 2012 11 57 49 AM PST Laminate Node Assignment 1 All Laminates Laminate_1 7 Show Color Values Show Labels F Show Only Laminate Part Hide Laminate Part Reset Select Nodes of Laminate E Show Display Options 33 Select the Laminates_1 entry from the list in the Laminate Assignment Panel Progressive Failure Analysis PFA Static Un notched Section 2 1 13 Coupon 34 35 36 37 38 39 S
7. 9E 02 7 66690E 02 1i 6 1352E 03 0 00000E 00 0 00000E 00 0 00000E 00 1 0163E 01 1 0225E 03 12 9 2028E 03 0 00000E 00 O 0000F 00 QO O000F 00 1 5440E 01 1 5338E 03 13 9 9697E 03 0 0000E 00 0 00000E 00 O 0000F 00 1 6768E 01 1 6616E 053 l4 1 0161E 04 O 0000F 00 O O000F 00 QO OO00F 00 1 7100E 01 1 6936E 053 Load Displacement data for node 165 from PFA Static Flat Coupon dis file Edit System Configurations to Change Format Settings If you wish to change the font size type or precision values that you see through GENOA GUI then do the following 118 Under the Project menu select Advanced System Settings 119 Change the entries under 3D Color Scale Number Format as you see fit 120 Exit and Save the project as explained earlier You have finished this tutorial of importing and editing GENOA model file running the Progressive Failure Analysis with default MHOST FE Solver and viewing the results
8. FE Model and print it in a separate text file Set true for Enable XYPlot option under Advanced Settings panel Set STRAIN and STRESS for X direction for node 145 as shown in the following Figure GENOA will save the data in a separate text file during the simulation project_name sig Note You can print stress strain data for a specific ply by entering ply number in the Ply Number column If left empty GENOA will print the laminate level stress and strain data in the text file Similarly set true for Enable Out Displacement option under Advanced Settings below Enable XYPlot option This option will allow you to print the total load nodal reaction load and nodal displacement for the selected nodes and directions Set 164 and X node number and direction as shown in the following Figure Node 164 is located on the right edge of the FE model GENOA will save the data in a separate text file during the simulation project_name dis Progressive Failure Analysis PFA Static Un notched Section 2 1 18 Coupon Step by Step Tutorials X Plot Output Parameters Number Type Direction Node Elem Ply Number 1 STRAIN X 145 2o ees kis S Out Displacement Output Files Number Node Direction 1 164 b Requesting output in text files during simulation Progressive Failure Analysis 67 Right click on Analysis node and select Progressive Failure Analysis option under Add as shown in the Figure below i T E Progressive Fai
9. ORCE X Ibf Individual node look up of node 164 with X Displacement Here we will generate stress strain data for element 22 in the FE model Uncheck Swap Axis Change the node number to 145 Select Stress Vs Strain option under Property Leave the default 11 under Laminate Stress and Ex under Laminate Strain options Laminate Stress vs Strain 200 000 175 000 150 000 125 000 100 000 fo 000 20 000 23 000 ese S11 lbf in 2 0 0000 0 0025 0 0050 0 0075 0 0100 0 0125 0 0150 0 01753 Ex El Snap Avis Individual element look up of node 145 Stress strain data Progressive Failure Analysis PFA Static Un notched Section 2 1 28 Coupon Step by Step Tutorials 112 Select Show Damage option near lower left corner of the screen Note This will allow you to monitor at what stress level damage initiations propagates and then ultimately fail Note Move the cursor and hold onto the point of interest in the graph and you will see the corresponding x and y values for the point on the graph Laminate Stress vs Strain 200 000 175 000 130 000 125 000 100 000 3 000 20 000 22 000 g E a a 0 0000 0 0025 0 00530 0 0075 0 0100 0 0125 0 0150 0 0175 Ex 11 Ibf in 2 007 87 640 707 Ao Damage A Damage Initiation Damage Propagation Fracture Initi
10. Progressive Failure Analysis PFA Static Un notched Coupon Section 2 1 1 Step by Step Tutorials PFA Static Un notched Coupon Case Description Example Location Model Description Material Description Objective of Analysis ASTM Number Control Type Analysis Type Unit System Solution Input Requirements FEA Solver Output from Analysis Composite coupon subjected to a tensile loading in dry conditions Tutorials gt Static gt PFA Static Nodes 287 Elements 240 Plate length 10 Plate width 1 5 and Plate thickness 0 033 Graphite Epoxy Ply properties are used lay up of 0 90 0 s and 0 0055 ply thickness Determine the ultimate failure load and associated failure modes ASTM D3039 Load Control Static Inch Second Pound STATIC UPDATE GEOMETRY TRUE Updated Lagrangian See PFA Case Control Keywords Section 3 2 of User Manual 1 Import FEM Model dat GENOA file 2 Assign Edit boundary and loading conditions 3 Assign Edit and verify material properties fiber matrix properties 4 Create Ply Schedule MHOST See PFA Case Control Keywords Section 3 2 of User Manual Structural deformations ply stresses and strains load displacement curve active failure modes at various load increments including damage initiation and progression fracture initiation and failure loads Progressive Failure Analysis PFA Static Un notched Section 2 1 2 Coupon Step
11. Trans Gut of plain Shear Strain Interactive Failure Criteria MDE Modified Distortion Energy TSAI Tsai Wu HILL Tsai Hill HOFF Hoffman HASH Hashin PUCK PUCK SIFT Strain Invariant Failure Theory Honeycomb Failure Criteria WRANE Wrinkling for Honeycomb CRMP Crimping for Honeycomb 27 Similarly in the Critical Fracture Criteria tab click on the Composite Default button to select the Section 2 1 11 Step by Step Tutorials default recommended failure criteria This will set the CFC Customized Failure Criteria to true Note A CFC criterion if activated automatically determines the primary failure criteria based on the loading direction in each ply When all the plies in the laminate meet this criteria the element consisting of this laminate is considered broken Now we will assign the failure criteria to the laminate ply layup that we were defining earlier 28 Choose FailCrit_1 from the drop down box in the Failure column for each ply Progressive Failure Analysis PFA Static Un notched Section 2 1 12 Coupon Step by Step Tutorials Material Type Fiber Matrix Temperature Thickness pe Fiber Volume Void Volume F in peress Fraction Fraction 0 57 0 02 Failure Strain Limit Fiber Matrix CARB EPOX 70 0 0055 NONE Fiber Matix CARB EPOX 70 0 0055 e f on f on hoe fotoe FberMatix CARE EPOX 70 oooss ZEN Fiber Matrix CARB EPOX 7 0 0
12. a Failure Criteria 24 Right click on the Failure tree node and select Add and then Failure option as shown in the following Figure Failure i ole na Je rr le Delete All Items Note This will add failure criteria FailCrit_1 as shown below ae Failure 1 25 Right click on the FailCrit_1 node and select Edit to review the damage and failure criteria assigned to the laminates 26 Inthe Damage Criteria tab click on the Composite Default button at the bottom of the panel to select the set the default recommended criteria Progressive Failure Analysis PFA Static Un notched Coupon Damage Criteria Critical Fracture Criteria Name Fiber Failure Criteria 5117 Longitudinal Tensile 511C Longitudinal Compressive F11C Fiber Micro Buckling R11C Fiber Crush D11C Delaminations Matrix Failure Criteria 5227 Transverse Tensile 522C Transverse Compressive S330 Normal Compressive 5125 In Plane Shear Delamination Failure Criteria 5337 Normal Tensile 5235 Transverse Normal Shear 135 Longitudinal Normal Shear RROT Relative Rotation Maximum Strain Based Failure Criteria EPS 117 Longitudinal Tension Strain EPS 11C Longitudinal Compression Strain Matrix Failure Criteria EPS22T Transverse Tension Strain EPS22C Transverse Compression Strain EPS337 Normal Tension Strain EPS33C Normal Compression Strain EPS 125 In plain Shear Strain EPS135 Long Out of plain Shear Strain EPS235
13. alysis PFA Static Un notched Section 2 1 22 Coupon Step by Step Tutorials Element Stress 82 83 84 85 86 Select Stress DG node under Analysis Results node in the tree Select Equilibrium Iterations from the drop down list box located near the bottom right of the screen Rewind the iteration to the beginning to see the initial stress 2 0451E 03 The initial stress Nx at Iteration 1 Drag through the iterations or press the play button and watch the stress change with respect to the color scale on the left X 6 99E 03 Stress Nx at iteration 14 stress during playback Click on different stress types one by one Nx Ny and Nxy You may also change the current iteration and play back the iteration animation while a particular stress type is selected Element Strain 87 Select Strain amp node under Analysis Results node in the tree 88 Choose Strain from the Results menu to view the different strain results strain il 1 000E 02 Strain Strain in mid plane Ex mode display at last equilibrium 14 iteration Ply Damage 89 Select Ply Damage node under Analysis Results node in the tree 90 Select All Iterations from the drop down list box located near the bottom right of the screen Progressive Failure Analysis PFA Static Un notched Section 2 1 23 Coupon Step by Step Tutorials 91 Change the current iteration to 5 where the first damage occurred 92 Selec
14. ation Fracture Propagation fo Damage Damage Initiation se Damage Propagation Fracture Initiation Fracture Propagation Export Graph to Text File Import Test Curve Clear Test Curve Swap Axis Individual node look up of node 145 Stress strain data Exporting Graph Data 113 114 115 You may export data throughout the GUI into different formats For any graph in any module of GENOA you may export the graph data into a text file or import data depending on some modules by clicking on the Export Graph to Text File button at the bottom or by selecting Export to Text File from the Graph menu Unselect Show Damage option near lower left corner of the screen Click on the Export Graph to Text File button at the bottom Type in a filename in the file dialog such as Stress Strain_n145 txt and press Export Data The text file data will look similar to below Progressive Failure Analysis PFA Static Un notched Section 2 1 29 Coupon Step by Step Tutorials 99859844 7oE 0 b eee te ay cat 234 ay MI ey le ll 1971720713E 04 f469450452E 04 3 Ema cat ONO Arla fe 0S Oo 52180984 26E 04 7 W2997 3436 1E 03 8 7156339251E 04 r 0707253180E 03 Oo 7640706855E 04 7 1114 6656E 03 o o125074460E 04 7 1929532920E 03 o 90938244 65E 04 Stress_Strain_n145 txt file generated on clicking Export Data button Saving the Project 116 Click Save item under the Project menu or you may select the same function by ri
15. ation 5 or enter 5 into the Iteration text box Progressive Failure Analysis PFA Static Un notched Section 2 1 21 Coupon Step by Step Tutorials Damage Node Damage Fiber Damage Only Matrix Damage Onty Delamination Damage Only 100 0 522T Transverse Tensile 100 0 INTR Interactive Failure Criteria Fractured Nodes Show All Damage List Damaged Nodes The Damage results model at Iteration 5 Note Transverse Tensile and Modified Distortion Energy damage criterion have occurred within the model at the highlighted elements marked in red This indicates that the 90 deg plies are failed due to matrix failure Note The element switches to red color even if one ply out of six plies is damaged 81 Advance the iterations further until you reach the last iteration Damage Node Damage Fiber Damage Only Matris Damage Onby Delamination Damage Only 100 0 5117 Longitudinal Tensile 100 0 511C Longitudinal Compressive 100 0 F171C Fiber Micro Buckling 100 0 5227 Transverse Tensile 100 0 INTR Interactive Failure Criteria Fractured Nodes The final failure results at the last Iteration Note The damage panel shows Longitudinal Tension failure that corresponds to fiber failure for O degree plies in the coupon The Longitudinal Compression appears because the fibers in the 90 degree plies are assumed to have buckled during the analysis after matrix failure Progressive Failure An
16. by Step Tutorials Summary of Results Damage Initiation Load 4314 0 Ibf Active damage modes Longitudinal tensile transverse tensile and modified distortion energy Final Failure Load 10161 4 Ibf Active failure modes Longitudinal tensile and compressive transverse tensile and modified distortion energy Introduction This tutorial demonstrates how to modify and edit a previously translated FE model in GENOA format and set if for performing the Static Progressive Failure Analysis using the default MHOST FE solver This example contains a standard un notched coupon and was originally prepared in PATRAN The model does not contain any boundary and loading conditions and any ply schedule information Note To see the solution and results for this tutorial please open the project from the Solutions library Launch GENOA 1 Start GENOA by executing it from the desktop or typing genoa in the command prompt Setup The first step is to import the model file which is already in GENOA format 2 Make sure the Unit System in the upper right corner is set to Inch Second Pound Note Depending upon the units that have been used to create FE models the units should be changed before preparing or importing the model if necessary Note The imported GENOA input file contained UNIT keyword to indicate the units lt Unit System 3 Right click on PFA Static Flat Coupon item under the Static tutorials and select
17. e left mouse button and drag a selection box around the right edge nodes of the mesh Note The right edge of the model consisting of 7 nodes will be highlighted yellow while the rest of the model nodes will be red Progressive Failure Analysis PFA Static Un notched Section 2 1 14 Coupon Step by Step Tutorials 42 From the Force panel select the Force X item in the force type list 43 Inthe Enter New Value field type in 255 6333 Ibf and click on the Apply to Selected Nodes The FE model will show directional arrows and a red gradient color at the right edge 44 To apply uniform loading we will assign double the value of 255 6333 Ibf to the middle nodes of the edge Using the mouse and Shift key select the middle five nodes Type in 511 2667 Ibf in the Enter New Value field in the Force panel and click on Apply to Selected Nodes button Note The scale bar located left side of the model view shows the values of the color in the coupons discretely for further verification BE 02 JSE U2 13E 02 1SE 02 JSE 02 1SE U2 BE U2 Note The user may have to define a smaller value as in GENOA this corresponds to incremental load and not the final load as is usually the case in other commercial FE solvers The FE model is now ready to have boundary conditions defined Boundary Conditions 45 46 47 Right click on Mesh node and select Boundary Conditions under Constraints and Add popup menus Note Y
18. e z direction of the elements in the FE model shown in the Figure below Ply 2 Ply 1 Shell Solid Element Note By default a single laminate is created as shown in the Laminates tree as Laminate_1 To add more laminates you would right click on the Laminates node and select Add from the popup menu For this tutorial we will edit the current default laminate 19 Right click on the Laminate_1 node and select Edit in the popup menu You may double click on the Laminate_1 node to view and edit it Progressive Failure Analysis PFA Static Un notched Section 2 1 9 Coupon Step by Step Tutorials B x Laminates 1 B Analysis H D Jobspooler 6 Export Rename J Duplicate Note The laminate editor will be displayed as shown below Void Volume Fraction Material Type Failure Strain Limit Temperature Thickness Angle Fiber Volume Fraction Dake Py Rone 20 Click on Add Ply Row button six times at the bottom of the Laminate Editor panel to add six layers in the laminate Note You may add delete cut copy insert and paste more plies in any configuration You may use the buttons at the bottom to add and delete ply rows or use the popup menu as shown below by right clicking on any selected row s Note Laminate Editor automatically determines the Fiber and Matrix names for each ply The user needs to update the Material Type Fiber and Matrix entries if wishes to have different mater
19. ements Allowed to Fracture is set to 2 The user should not change these parameters They should be used by advance GENOA users only to overcome convergence issues during the simulation Description Value 4 Pa Number of Nodes Elements Allowed to Damage Number of Nodes Elements Allowed to Fracture Number of Iterations to Run static Parameters Post Buckling Enabled Unloading Enabled se E JUME Analysis Mode Parameters Settings 60 Double click on Advanced Settings node under Analysis Mode node or right click it and select Edit 61 Under Advanced Settings panel set True for Print Running Stress Print Running Strain and Print Displacement by clicking the left mouse button on the true false cell only once 62 Select All Plies next Ply Stress and Ply Strain options Progressive Failure Analysis PFA Static Un notched Section 2 1 17 Coupon 63 64 65 66 Step by Step Tutorials Print Options Section Print Multiple Large Fies fake true Print Running Strain true Print Displacement true false false false false false false false false Ply Stress ALL FLIES Ply Strain ALL PLIES Fier Stres hoe Matrix Stress NONE Ply Principal Stress NONE Note GENOA always sets these basic print options in previous two instructions to true by default and they were intentionally set to false as part of this exercise Note You can request to print stress strain data for a specific node element in the
20. ght clicking on the Project node in the tree to show the popup menu 117 Exit the Project by selecting Exit under Project menu and then confirm by clicking on Save button Check Previously Requested Stress Strain and Displacement Files Recall that we requested GENOA to print stress strain for node 145 and load displacement for node 165 in separate ASCII files project_name sig and project_name dis respectively You should see these additional files in your working directory PFA Static Flat Coupon_PFA where this simulation was run on your computer Stress_Strain data for node 145 from PFA Static Flat Coupon sig file Progressive Failure Analysis PFA Static Un notched Section 2 1 30 Coupon Step by Step Tutorials DISPLACEMENTS FOR USER SELECTED NODES DISPLACE FORCE IHTER FORCE 2 FORCE Y TIGL PRESSURE 164 1 Ife a 0 O QO000F 00 0 0000E 00 O 0000F 00 O0 0000F 00 O QO000E 00 O 0000E 00 1 3 0676E 05 0 0000E 00 O 0000F 00 O OO00E 00 4 9986E O2 1127E 02 2 3 86345E 03 0 0000E 00 O 0000F 00 0 00000E 00 6 2549ER 02 6 3906E 02 3 4 21179E 03 0 0000E 00 0 00000E 00 0 00000E 00 6 8639R 02 7 02499E 02 4 4 31138E 03 0 0000E 00 0 0000E 00 0 00000E 00 7 0412E 02 7 18977E 02 Y 4 33708E 03 0 0000E 00 0 00000E 00 0 00000E 00 7 0623E 02 7 22496E 02 o 4 36117E 03 0 0000E 00 0 00000E 00 0 00000E 00 7 1233E 02 7 26966E 02 9 4 40977E 03 0 0000E 00 0 00000E 00 0 00000E 00 7 2054E 02 7 33495E 02 10 4 60114E 03 0 00000E 00 0 00000E 00 0 00000E 00 7 533
21. ial assigned to each ply Craton Void Volu in Degrees Fraction Fraction 1 moer Marix CAR 0 0055 0 emer ORs ex mass one ne noe fears fone eax moms 0 PX etto p Ye Fiber Matrix CARB EPOX 70 0 0055 o Ta FberMatrx cars x w ows o a Material Ty Fiber Matrix are geg mn Strain Li gt 6 21 Change the Fiber Volume Fraction to 0 57 57 by clicking and editing the cell of each six rows 22 Similarly update the Void Volume Fraction to 0 02 2 by clicking and editing the related cells 23 Now change the Angle Degrees entry of each ply to represent 0 90 0 s layup Progressive Failure Analysis PFA Static Un notched Section 2 1 10 Coupon Step by Step Tutorials E a r Fiber Volu Void Volu in comes iFrachon Crecten 1 rea Rete CARB 2 Fer Matix cars EPOK o o 00ss af osr oo NONE NONE Fiber Matrix CARB EPOX 70 0 0055 O 057 002 NONE NONE _Fiber Matrix CARB EPOX 70 00055 oo l 002 L NONE ONONE Fb Mat CARB EPOX 70 0 0055 90 0 57 0 02 datas FiberMax CARE EPOX 70 0 0055 o osz ooz NONE NONE Final Ply Schedule after updating the angle thickness and material assignment for each ply Note You may choose to define un symmetric ply lay Note You may mix different Material Types Ply Fiber Matrix or Matrix in one laminate layup definition Adding
22. ight click on the new Fiber material and select Rename Or you may rename it by pressing F2 key while the Fiber tree node is selected Enter the new name CARB Note The material name can be any length lower and upper case You can also use numerals with the alphabets El Materials 1 Fiber 1 Duplicate To Library F Strain Lin Delete All Items Laminates X Ha m m oe Note In this exercise we will use effective fiber matrix properties as input obtained from unidirectional ply properties Please refer to MCQ Composites to learn how to generate effective fiber matrix properties from unidirectional ply properties usually obtained from test or literature Note For this exercise the material properties are assumed to be valid for 70 F room temp T To enter the fiber material properties right click on the CARB node and select Add Property from the popup menu 8 Navigate and select Mechanical option to add Modulus Poisson s Ratio and Strength as shown below Progressive Failure Analysis PFA Static Un notched Section 2 1 5 Coupon 10 11 Step by Step Tutorials ee ry Materials 1 Si Fiber 1 P Add Property Add P Add Property gt H 2 a General Temperature Sets ic Modulus Thermal t Poisson Ratio Electrical t E Strength Rename Duplicate To Library Hyqral Delete All Items Structural Damping Stress Strain Curve LCN T i a al
23. lements force loading moment pressure equilibrium status number of damaged nodes and number of fracture nodes The rows highlighted in green are iterations that have reach equilibrium state Elements Nodes Force X Force Y Force Z MomentX MomentY MomentZ Pressure Load Damage Fracture Status 240 287 3 068E4 03 0 000E 00 0 000E 00 0 000E 00 0 000E 00 0 000E 00 0 000E 00 3 06858E 03 0 0 Equilibrium 240 3 835E 03 3 835E 03 0 Equilibrium 0 000600 0 0006 00 4 3146403 0 0 lEqulbrium 24 287 4338403 0 000E 00 0 000E 00 0 000400 0 000E 00 0 00000 0 000E 00 4 338E 03 287 o Damaged 24 287 4 338403 0 000E 00 0 000E 00 0 000400 0 000E 00 0 00000 0 000E 00 4 338E 03 287 0 Damaged 0 000 00 0 000E 00 0 000 00 4 338E403 287 0 Eau brium 0 000600 0 000E 00 0 000E 00 4 362E 03 257 o Equ brium 0 0006 00 9 2036403 287 0 fEquibrium 0 000640 9 976403 287 0 Equilibrium 1 The log indicates that damage in the coupon initiates at 4314 0 Ibf and final failure happens at approximately 10161 4 Ibf Note the damage initiation and final failure load values should be read for equilibrium iteration Click on the View Equilibrium Iterations Only button The log will show only the equilibrium iteration rows highlighted in green Click on the View All Iterations button The log will show all the iteration rows default Progressive Failure
24. lure Analysis y Filament Winding Parametric Carpet Plots i A amp B Basis Allowables Simulation oat ol ow Y E Probabilistic Analysis Parametric Robust Design 68 Right click on the Progressive Failure Analysis node and select Run Analysis Saving the Project 69 Save the current project and all of the changes in the memory Choose Save from the Project menu Analysis Results After the analysis is complete the program will automatically show the Results Log screen But if you wish to load the current results during the analysis then you may press the Reload Results menu item under the popup menu for the Analysis Results node in the tree You may reload the results at any time if you believe that the results are not current or updated correctly Progressive Failure Analysis PFA Static Un notched Section 2 1 19 Coupon Step by Step Tutorials Ea sos ResultsLog Reload Results p GF Mesh e Energy Graph When there are results to be loaded there will be additional nodes under the Analysis Results node as shown following Figure ae Analysis Results aa Results Log aoe Energy Graph 7 Element Graph Results Log 70 Iteration 71 72 73 Bal Ga Ro ES e s a n w Double click on the Results Log node to view the iteration log Note The Results Log will display iteration of the analysis with the current state of the number of nodes e
25. ou may access the same panel by clicking on the Boundary Conditions Icon on left of the model view window Notes The Force panel will switch to the Boundary Conditions panel The Nodes panel should still be active since we want to continue selecting nodes The FE model should be filled with a solid blue color Press and hold the Shift key on the keyboard then click left mouse button to select the left edge nodes of the model by dragging a selection box as was done earlier to assign force Note The left edge of the model consisting of 7 nodes will be highlighted yellow while the rest of the model nodes will be red From the Boundary Conditions panel select the Boundary X item in the type list and click the Apply to Selected Nodes The left edge will be fixed in the X direction Progressive Failure Analysis PFA Static Un notched Section 2 1 15 Coupon Step by Step Tutorials Boundary Condition X direction on the left edge 48 Similarly select the bottom corner nodes on the left and right edges of the FE model 49 50 51 52 53 54 Note You can use CTRL key on the keyboard to add nodes to existing selection However the Shift key is for making new selection and ignoring any existing selection From the Boundary Conditions panel select the Boundary Y item in the type list and click the Apply to Selected Nodes The node will be fixed in the Y direction which is sufficient for this direction on this model
26. t Laminate_1 in under Select Laminate subpanel 93 Click and highlight all six plies in the ply window by using the Ctrl or Shift key to show all six plies stacked in the default Z direction By default the All Damages item is selected 94 Enter 2 0 for Offset Distance 95 Rotate the mesh if necessary to view the plies from top to bottom as shown below I Damages I Damages I Damages I Damages I Damages I Damages Ply by Ply Damage Initiation results at iteration 5 Note Here you can examine which ply damage occurred first and the ply damage growth throughout the analysis iterations Note The 90 degree plies failed due to matrix failure criteria transverse tension 96 Turn on the Isolate Damage Areas checkbox to make all the non damaged areas transparent This is useful for examining more complex solid models where damage may occur internally 97 You may also change the Offset Distance proportion to 0 5 to reduce the spacing further ll Darnages Damages li Darmages All Damages All Damages a Iteration 5 damage initiation b Iteration 15 Final Failure Progressive Failure Analysis PFA Static Un notched Section 2 1 24 Coupon Step by Step Tutorials Ply Damage with Isolate Damage Areas enabled to show transparency Ply Stress 98 Select Ply Stress SJ node under Analysis Results node in the tree 99 Click and highlight the all six plies in the ply window by using the Ctrl or Shift key to show all si
27. tep by Step Tutorials Click on the Nodes icon on the left toolbar or select Nodes option under Display menu press the spacebar on the 3D model view Note Since MHOST is our Solver for this exercise you selected nodes in the FE Model For all other FE Solvers you will select the elements for assigning the Laminate card Expand the Node Selection arrow icon on Nodes panel to show the node selection panel Hold the Shift key and press the left mouse button to drag a box to select all the nodes in the model The list of selected nodes is shown under the node selection list in the Nodes panel e g 1 287 You may also select all the nodes by pressing the Select All Nodes button in the Nodes panel With Laminate_1 selected in the Laminate Assignment panel click on Apply to Selected Nodes button in the Nodes panel This will assign the laminate to the selection of nodes Note Blue color will switch to red color indicating that laminate assignment process was successful Click on Select None button under the Nodes panel to unselect the selected nodes Close the Laminate Assignment panel Notes We will keep the Nodes panel open for the force loading discussed next Force Loading 40 41 Click on the Force icon on the left toolbar Note you can also access the Force panel by right clicking on Mesh node and selecting Nodal Force under Load and Add popup menus While holding the Shift key on the keyboard click on th
28. tep by Step Tutorials Percentage Damage Volume Damage Volume 33 DERR Total DERR 30 Damage Energy Strain Energy 25 if 2 2 20 uy 1s a 10 oC 3 ee g 2 200 3 000 7o00 10 000 FORCE LBF No Damage Damage Initiation Damage Propagation A Fracture Initiation Fracture Propagation Pressure lb fitin 2 aa sna as Percent Damage Volume graph Note The x axis domain represents the iterations default while the y axis range shows the current item selected Damage Volume Here the graph shows a significant rise in damage increase around 4314 0 Ibf Node Graph 105 Click on the Node Graph node 106 Type in one of the edge nodes that the force was being applied to such as node 164 107 Select Force X Ibf under Domain Note The forces shown are total forces in the x direction in the whole FE model and not the nodal reaction forces Note The Displacement is default selection under Property panel and X direction under Displacement Type 108 Check Swap Axis option near lower right corner Progressive Failure Analysis PFA Static Un notched Section 2 1 27 Coupon 109 110 111 Step by Step Tutorials Displacement in of Nodes 164 10 000 9 000 8 000 7 000 6 000 2 000 4 000 3 000 2 000 1 000 0 ee ee a ae 0 000 0 025 0 050 0 075 0 100 0 145 0 150 0 175 x 164 Values Displacement F
29. under the Materials tree node A Matrix material will be added to the matrix list 5 49 Materials 1 a an Fiber 1 Add d W Matrix iT Delete All Items From Library E Braid 0 13 Right click on the new Matrix material and select Rename Or you may rename it by pressing F2 key while the Matrix tree node is selected Enter the new name EPOX Note The material name can be any length lower and upper case You can also use numerals with the alphabets ct P G Matrix 1 Ply 0 Add Property Temperature Sets Rename Duplicate a T 14 To enter the matrix material properties right click on the EPOX node and select Add Property from the popup menu Progressive Failure Analysis PFA Static Un notched Section 2 1 7 Coupon Step by Step Tutorials 15 Navigate and select Mechanical option to add Modulus Poisson s Ratio and Strength as shown below ae Matrix 1 Add Property General t E Mechanical E Fiber Matrix Interphase Properties Poisson Ratio e Thermal E Strength A ri Temperature Sets E et r IE Rename Duplicate Note the present tutorial is for PFA static analysis in dry condition only mechanical properties are considered and other hygral thermal electrical properties can be ignored 16 You should see the following after adding the Mechanical option i a Matrix 1 op Description None boon
30. x plies stacked in the default Z direction By default the Ply Stress 11 item is selected 100 Click and highlight Ply Stress 11 and then Ply Stress 22 3 0629E 05 9 6119E 03 2 267 rE 03 7 8806E 03 6 1492E 03 1 5124E 05 fF 18E 04 4 4179E 03 3 8059E 03 2 6865E 03 a Ply Stress 11 b Ply Stress 22 Ply Stress type results at last iteration 15 Ply Strain 101 Select Ply Strain Sy node under Analysis Results node in the tree 102 Click and highlight the all six plies in the ply window by using the Ctrl or Shift key to show all six plies stacked in the default Z direction By default the Ply Strain EPS11 item is selected Progressive Failure Analysis PFA Static Un notched Section 2 1 25 Coupon Step by Step Tutorials 1 7100E 02 1 2000E 02 6 9000E 03 1 8000E 03 X 3 3000E 03 Ply Strain Ply Strain EPS 11 results at last iteration 15 Results Graphs 103 104 Let s examine the results data more closely Double click on the Energy Graph node under the Analysis Results node Click on the Damage Volume item for Percent Damage Volume under Output Graph Section and Force Ibf under Domain Section Note This Percent Damage Volume is the ratio of the damaged elements in the FE model to the total number of elements times 100 Progressive Failure Analysis PFA Static Un notched Section 2 1 26 Coupon S
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