Description: Defines the global plies and properties of an n-ply composite material laminate for CHEXA and CPENTA solid elements.
Format:
Example:
Field | Definition | Type | Default | ||||||||||
---|---|---|---|---|---|---|---|---|---|---|---|---|---|
PID | Property identification number. | Integer > 0 | |||||||||||
MCID | Identification number of the material coordinate system. See Remarks 5 and 6. | Integer ≥ -1 or blank | See Remark 5 | ||||||||||
XZDIR | Ply orientation reference material axis and element orientation, one of the following character variables: 12, 13, 21, 23, 31, or 32. See Remark 6. | Integer | 13 | ||||||||||
SB | Allowable inter-laminar shear stress of the bonding material (allowable interlaminar shear stress). Required if bond shear failure index/strength ratio is desired. | Real > 0.0 | |||||||||||
NB | Allowable inter-laminar normal stress of the bonding material. | Real > 0.0 | |||||||||||
TREF | Reference temperature. See Remark 4. | Real | 0.0 | ||||||||||
GE | Structural element damping coefficient. See Remarks 12 and 13. | Real | 0.0 | ||||||||||
GPLYIDi | User defined global ply identification number. | Integer > 0 | Ply number | ||||||||||
MIDi | Material identification number of the various plies. The plies are identified by serially numbering them from 1 at the bottom layer. The MIDs must refer to MAT1, MAT8, MAT9, or MAT12 Bulk Data entries. See Remark 11. | Integer > 0 | |||||||||||
Ti | Ply thickness. See Remarks 2 and 7. | Real or blank | T1 required | ||||||||||
THETAi | Orientation angle of the longitudinal direction of each ply with the material axis of the element. The plies are numbered serially starting with 1 at the bottom layer. The bottom layer is defined as the surface with the largest -Z value in the element coordinate system. See Remark 6. | Real or blank | 0.0 | ||||||||||
PLYFTi | Ply failure theory. The following theories are allowed. (If blank and not specified on the referenced MIDi entry, then no failure calculation is performed.)
|
Character or blank | |||||||||||
ILFTi | Inter-laminar failure theory. The following theories are allowed. (If blank, then both calculations are performed.)
|
Character or blank | Both | ||||||||||
SOUTi | Stress or strain output request, one of the following character variables: YES or NO. | Character | NO |
Remarks:
Theory | Failure Index | Remarks |
---|---|---|
Hill |
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Orthotropic materials with equal strengths in tension and compression. |
Hoffman |
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Orthotropic materials under a general state of plane stress with unequal tensile and compressive strengths. |
Tsai-Wu |
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Orthotropic materials under a general state of plane stress with unequal tensile and compressive strengths. |
Max Stress | Max
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None |
Max Strain | Max
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None |