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C2-1NAS113, Chap. 2 , November 2003
Chapter 2
MAKING A COMPOSITE MODEL
C2-2NAS113, Chap. 2 , November 2003
CONTENTSPly Definition pg. 2-3Tape Plies pg. 2-4MAT8 bulk data entry pg. 2-5Patran 2D Orthotropic pg. 2-6Composite Material pg. 2-7PCOMP bulk data entry pg. 2-8Patran Composite pg. 2-10CQUAD4 bulk data entry pg. 2-11Patran Composite Properties pg. 2-12Patran Material Coord. System pg. 2-13Nastran Input File pg. 2-15Nastran Ply Stress Output pg. 2-16Patran Ply Output Request pg. 2-17Patran Ply Stress Results pg. 2-18Workshop 1 – Creating a Composite pg. 2-19
C2-3NAS113, Chap. 2 , November 2003
PLY DEFINITION
Typically a ply is a flat group of fibers imbedded in a matrix.The matrix is usually an isotropic material that holds the fibers together.In a ply called a tape, the fibers are unidirectional.In a ply called a cloth, the fibers are woven at 0 and 90 degree directions.
C2-4NAS113, Chap. 2 , November 2003
TAPE PLIESFiber:
Unidirectional in tapeDirection is the 1 axis of the ply coordinate system
Matrix:Glue that holds fibers togetherMatrix direction is the 2 axis90 degrees to the 1 axis
Material properties are: 2D orthotropic material in Patran MAT8 in Nastran
C2-5NAS113, Chap. 2 , November 2003
MAT8 BULK DATA ENTRYDefines the ply orthotropic properties.
Elastic properties are E1, E2, NU12, G12, G1Z, G2Z.Allowables are Xt, Xc, Yt, Yc, S. Use STRN=1.0 if allowables are in units of strain.F12 is for the Tsai-Wu failure theorem.Thermal coefficients of expansion are A1 and A2, The MAT8 TREF reference temperature is not used since it is overridden by the PCOMP TREF,Density is RHO, The MAT8 GE structural damping is not used since it is overridden by the PCOMP GE
The example below is typical for a graphite/epoxy tape.
1.3-41.6+61.6+61.6+60.352.+620.+61MAT8
RHOG2ZG1ZG12NU12E2E1MIDMAT8
10987654321
1.25+41.2+41.1 +41.2+51.3+54.5-6-2.3-7
SYcYtXcXtTREFA2A1
.bdf file extract
STRNF12GE
mat8, 1, 20.+6, 2.+6, 0.35, 1.0+6, 1.0+6, 1.0+6, 1.3-4,++, -2.3-7, 4.5-6,, 1.3+5, 1.2+5, 1.1+4, 1.2+4, 1.25+4
C2-6NAS113, Chap. 2 , November 2003
PATRAN 2D ORTHOTROPIC
Materials:
Create/ 2d Orthotropic/ Manual Input
Material Name
Input Properties
Linear Elastic
Apply
Input Properties
Failure
Apply
C2-7NAS113, Chap. 2 , November 2003
COMPOSITE MATERIALStack of pliesEach ply has a different direction, material, and thicknessComposite properties are calculated in the material coordinate system (Xm, Ym,Zm)
Zm is the same as the element Z axis (Ze)Right hand rule of grid ordering, G1,G2,G3,G4
Xm is in the direction of the 0 degree plyPositive angles are defined by right hand rule around Zm
C2-8NAS113, Chap. 2 , November 2003
PCOMP BULK DATA ENTRYDefines the composite layup.
0.0HILL5000.01PCOMP
LAMGETREFFTSBNSMZ0PIDPCOMP
10987654321
YES45.00.00541YES0.00.00541
SOUT2THETA2T2MID2SOUT1THETA1T1MID1
90.00.00541
ect.SOUT3THETA3T3MID3
Z0 is composite offset. Use default = -(composite thickness)/2
NSM is nonstructural massSB is allowable interlaminar shear stress
Put as Bonding Shear Stress in Patran 2D Orthotropic Material (page 2-6)
FT is the ply failure theoremTREF is reference temperature
Overrides TREFs on ply MAT8s
GE is element dampingOverrides GE on ply MAT8s
LAM is layup optionsMIDi is ply material ID
MAT8 ID
Ti is ply thicknessTHETAi is ply angleSOUTi is data recovery option
C2-9NAS113, Chap. 2 , November 2003
PCOMP BULK DATA ENTRY (cont.)The example composite below is an 8 ply layup, symmetric about it’s centerline, with an equal number of plies in each of the 0, +45, 90 degree directions.
.bdf file extract
PCOMP, 1,,, 5000., HILL, 1, .0054, 0., YES, 1, .0054, 45., YES, 1, .0054, -45., YES, 1, .0054, 90., YES, 1, .0054, 90., YES, 1, .0054, -45., YES, 1, .0054, 45., YES, 1, .0054, 0., YES
C2-10NAS113, Chap. 2 , November 2003
PATRAN COMPOSITE
Materials:
Create/ Composite/ Laminate
To create a ply, click on a ply material in Existing Materials. Repeat for each of the plies
Thickness for all layers: 0.0054
Orientations: 0 45 –45 90 90 –45 45 0
Load Text Into Spreadsheet
Apply
C2-11NAS113, Chap. 2 , November 2003
CQUAD4 BULK DATA ENTRY
Defines the composite plate.Material coordinate system can be defined one of two ways:
MCID – (integer) - ID of a user defined coordinate system who’s X-axis is projected onto the element to define the element’s material coordinate system’s X-axis. This along with the Z-axis of the element coordinate system defines the material coordinate system.THETA – (real) - an angle between the G1G2 vector of the element and the X-axis of the material coordinate system. The positive sense of this angle is the right hand rule direction around the element’s Z-axis.
99432111CQUAD4
ZOFFSTHETA or MCID
G4G3G2G1PIDEIDCQUAD4
10987654321
CQUAD4, 1, 1, 1, 2, 5, 4, 99
CQUAD4, 1, 1, 1, 2, 5, 4, 25.0
C2-12NAS113, Chap. 2 , November 2003
PATRAN COMPOSITE PROPERTIES
Properties:
Create/ 2D/ Shell
Property Set Name
Option: Laminate
Input Properties
Click on Mat Prop Name Icon to select the material
Click on coord. sys. for projection to material coord. sys.
OK
Select elements
Apply
C2-13NAS113, Chap. 2 , November 2003
PATRAN MATERIAL COORD. Z-AXIS
Elements:
Verify/ Element/ Normals
Draw Normal Vectors
Apply
C2-14NAS113, Chap. 2 , November 2003
PATRAN MATERIAL COORD. X-AXIS
Properties:
Show/ Shell
Orientation Angle
Apply
C2-15NAS113, Chap. 2 , November 2003
GRID 1 0. 0. 0.GRID 2 0. .5 0.GRID 3 0. 1. 0.GRID 4 .5 0. 0.GRID 5 .5 .5 0.GRID 6 .5 1. 0.GRID 7 1. 0. 0.GRID 8 1. .5 0.GRID 9 1. 1. 0.$ SPC1,1,1235,1SPC1,1,135,2,3$ FORCE 1 3 500. 0. 1. 0.FORCE 1 6 500. 0. 1. 0.FORCE 1 6 500. 0. 1. 0.FORCE 1 9 500. 0. 1. 0.FORCE 1 7 250. 1. 0. 0.FORCE 1 8 250. 1. 0. 0.FORCE 1 8 250. 1. 0. 0.FORCE 1 9 250. 1. 0. 0.FORCE 1 7 250. 0. 1. 0.FORCE 1 8 250. 0. 1. 0.FORCE 1 8 250. 0. 1. 0.FORCE 1 9 250. 0. 1. 0.$ CORD2R, 99,, 0., 0., 0., 0., 0., 1., 0., 1., 0.ENDDATA
SOL 101CENDTITLE = Composite Workshop Chapter 2 - Sample Composite Input
SPC = 1LOAD = 1DISP = ALLSTRESS =ALL
$BEGIN BULKPARAM, POST, -1$ PCOMP, 1,,, 5000., HILL, 1, .0054, 0., YES, 1, .0054, 45., YES, 1, .0054, -45., YES, 1, .0054, 90., YES, 1, .0054, 90., YES, 1, .0054, -45., YES, 1, .0054, 45., YES, 1, .0054, 0., YESMAT8, 1, 2.+7, 2.+6, .35, 1.+6, 1.+6, 1.+6,,,,130000., 120000., 11000., 12000., 12500.$ CQUAD4 1 1 1 2 5 4 99CQUAD4 2 1 2 3 6 5 99CQUAD4 3 1 4 5 8 7 99CQUAD4 4 1 5 6 9 8 99$
NASTRAN INPUT FILE.dat file extract
Large field format on PCOMP continuation fields allows easier cutting and pasting of plies
C2-16NAS113, Chap. 2 , November 2003
S T R E S S E S I N L A Y E R E D C O M P O S I T E E L E M E N T S ( Q U A D 4 )ELEMENT PLY STRESSES IN FIBER AND MATRIX DIRECTIONS INTER-LAMINAR STRESSES PRINCIPAL STRESSES (ZERO SHEAR) MAXID ID NORMAL-1 NORMAL-2 SHEAR-12 SHEAR XZ-MAT SHEAR YZ-MAT ANGLE MAJOR MINOR SHEAR
0 1 1 2.55820E+05 2.81603E+04 2.73019E+04 0.0 0.0 6.74 2.59049E+05 2.49319E+04 1.17058E+050 1 2 4.96222E+05 1.19674E+04 -2.69492E+03 0.0 0.0 -0.32 4.96237E+05 1.19524E+04 2.42142E+050 1 3 -3.72387E+04 4.79000E+04 2.69492E+03 0.0 0.0 88.19 4.79852E+04 -3.73239E+04 4.26546E+040 1 4 2.03163E+05 3.17071E+04 -2.73019E+04 0.0 0.0 -8.83 2.07406E+05 2.74647E+04 8.99705E+040 1 5 2.03163E+05 3.17071E+04 -2.73019E+04 0.0 0.0 -8.83 2.07406E+05 2.74647E+04 8.99705E+040 1 6 -3.72387E+04 4.79000E+04 2.69492E+03 0.0 0.0 88.19 4.79852E+04 -3.73239E+04 4.26546E+040 1 7 4.96222E+05 1.19674E+04 -2.69492E+03 0.0 0.0 -0.32 4.96237E+05 1.19524E+04 2.42142E+050 1 8 2.55820E+05 2.81603E+04 2.73019E+04 0.0 0.0 6.74 2.59049E+05 2.49319E+04 1.17058E+050 2 1 2.20297E+05 -1.59550E+04 9.95088E+03 0.0 0.0 2.41 2.20715E+05 -1.63734E+04 1.18544E+050 2 2 9.15727E+04 -7.28449E+03 -2.31267E+04 0.0 0.0 -12.54 9.67154E+04 -1.24272E+04 5.45713E+040 2 3 -1.02861E+05 5.81209E+03 2.31267E+04 0.0 0.0 78.47 1.05290E+04 -1.07578E+05 5.90535E+040 2 4 -2.31585E+05 1.44826E+04 -9.95088E+03 0.0 0.0 -87.69 1.48844E+04 -2.31987E+05 1.23436E+050 2 5 -2.31585E+05 1.44826E+04 -9.95088E+03 0.0 0.0 -87.69 1.48844E+04 -2.31987E+05 1.23436E+050 2 6 -1.02861E+05 5.81209E+03 2.31267E+04 0.0 0.0 78.47 1.05290E+04 -1.07578E+05 5.90535E+040 2 7 9.15727E+04 -7.28449E+03 -2.31267E+04 0.0 0.0 -12.54 9.67154E+04 -1.24272E+04 5.45713E+040 2 8 2.20297E+05 -1.59550E+04 9.95088E+03 0.0 0.0 2.41 2.20715E+05 -1.63734E+04 1.18544E+050 3 1 -5.90459E+04 1.03837E+04 8.14704E+03 0.0 0.0 83.40 1.13269E+04 -5.99891E+04 3.56580E+040 3 2 1.11984E+05 -1.13646E+03 9.35916E+03 0.0 0.0 4.70 1.12753E+05 -1.90558E+03 5.73294E+040 3 3 -4.72039E+04 9.58604E+03 -9.35916E+03 0.0 0.0 -80.88 1.10887E+04 -4.87066E+04 2.98976E+040 3 4 1.23826E+05 -1.93411E+03 -8.14704E+03 0.0 0.0 -3.69 1.24352E+05 -2.45970E+03 6.34056E+040 3 5 1.23826E+05 -1.93411E+03 -8.14704E+03 0.0 0.0 -3.69 1.24352E+05 -2.45970E+03 6.34056E+040 3 6 -4.72039E+04 9.58604E+03 -9.35916E+03 0.0 0.0 -80.88 1.10887E+04 -4.87066E+04 2.98976E+040 3 7 1.11984E+05 -1.13646E+03 9.35916E+03 0.0 0.0 4.70 1.12753E+05 -1.90558E+03 5.73294E+040 3 8 -5.90459E+04 1.03837E+04 8.14704E+03 0.0 0.0 83.40 1.13269E+04 -5.99891E+04 3.56580E+040 4 1 8.79761E+04 9.55942E+01 1.42040E+04 0.0 0.0 8.96 9.02149E+04 -2.14316E+03 4.61790E+040 4 2 1.69212E+05 -5.37626E+03 -5.88892E+03 0.0 0.0 -1.93 1.69411E+05 -5.57467E+03 8.74926E+040 4 3 -1.08326E+05 1.33180E+04 5.88892E+03 0.0 0.0 87.23 1.36024E+04 -1.08610E+05 6.11062E+040 4 4 -2.70896E+04 7.84613E+03 -1.42040E+04 0.0 0.0 -70.44 1.28923E+04 -3.21357E+04 2.25140E+040 4 5 -2.70896E+04 7.84613E+03 -1.42040E+04 0.0 0.0 -70.44 1.28923E+04 -3.21357E+04 2.25140E+040 4 6 -1.08326E+05 1.33180E+04 5.88892E+03 0.0 0.0 87.23 1.36024E+04 -1.08610E+05 6.11062E+040 4 7 1.69212E+05 -5.37626E+03 -5.88892E+03 0.0 0.0 -1.93 1.69411E+05 -5.57467E+03 8.74926E+040 4 8 8.79761E+04 9.55942E+01 1.42040E+04 0.0 0.0 8.96 9.02149E+04 -2.14316E+03 4.61790E+04
NASTRAN PLY STRESS OUTPUTPrinted in the f06 file if STRESS=ALL or STRAIN=ALL Case Control Commands are used.
.f06 file extract
C2-17NAS113, Chap. 2 , November 2003
PATRAN PLY OUTPUT REQUEST
Analysis:
Analyze/ Entire Model/ Full Run
Translation Parameters/ OP2Subcases/ Create
Output Requests/ Advanced/ Element Stress
Ply Stresses
OK
Apply
C2-18NAS113, Chap. 2 , November 2003
PATRAN PLY STRESS RESULTS
Analysis:Access Results
Read Output2
Results:Create/
Quick PlotResult/
Stress TensorPosition/
Layer 1Quantity/
X ComponentSelect Deformation
Result:Displacements,
TranslationalApply
C2-19NAS113, Chap. 2 , November 2003
Go to WS1 in your workshop booklet
Workshop 1 – Creating a Composite