Users:General FEM Analysis/Elements Reference/Shell9 Composite
The element formulation is based on the Shell8. It contains further developments for layered composite shells.
Contents |
Input Parameters
Parameter Description
| Compulsory Parameters | ||
| Parameter | Values, Default(*) | Description |
|---|---|---|
| MAT | EL-MAT int | Linking to a material input block |
| INT_TYPE_SHELL9 | FULL | Control of integration type |
| ANS | NONE, Q, T, QT, TQ | Assumed Natural Strains (ANS) method:
|
| EAS | M,B,T,Q,S | Enhances Assumed Strains (EAS) method
|
| FORCE | XYZ, RST_ORTHO, RST, MAT_DIRECTION | Output control for stress constraints
|
| SDC | real | condition factor for director length, recommended value: 1.0 |
| MATERIAL_ANGLE | real | Fiber orientation angle. The angle is determined with respect to the element's edge from Node 1 to Node 2. |
| ROTATORIC_DOFS | DIR_DIFF, GLOB_6 | Switch between director and rotational degrees of freedom. |
| STRESS_OUTPUT | PRIN_VM, SIG_EPS | Stress output type
|
| STRESS_EVAL | GP, SURF | Stress evaluation location.
|
| Optional Parameters | ||
| Parameter | Values, Default(*) | Description |
| THICKNESS | real | Element thickness. This parameter is not compulsory, as the thickness can also be described via nodal values. |
| MATERIAL_DIRECTION | real,real,real | Fiber orientation with respect to the global Cartesian coordinate system. The value should be given as vector components. |
| PROJECTION | DIRECTOR, X-AXIS, Y-AXIS, Z-AXIS | Used projection method to calculate the material direction which is defined by the variable "MATERIAL_DIRECTION" |
| FAIL_ID | int | Failure criterion ID |
In addition it is possible to define layer properties individually. Below is a sample input deck for this element.
Example of a Complete Input Block
EL-PROP 1: SHELL9_COMPOSITE INT_TYPE_SHELL9 = FULL SDC = 1.0 EAS = 4,4,4,4,4 !4,4,4,4,4 !LIN:4,4,4,4,4 NLN:0,0,0,0,0 ANS = NONE FORCE = MAT_DIRECTION !RST !XYZ !RST_ORTHO !MAT_DIRECTION ! MATERIAL_ANGLE = 0 ! orientated wrt edge 1-2 MATERIAL_DIRECTION = 0, 0, 1 ! global cartesian PROJECTION = DIRECTOR ! Y-AXIS Z-AXIS FAIL_ID = 1,2 !------------------- ROTATORIC_DOFS = DIR_DIFF ! GLOB_6 STRESS_OUTPUT = PRIN_VM !PRIN_VM SIG_EPS STRESS_EVAL = GP !GP SURF !------------------- MAT=EL-MAT 1 THICK=0.5 THETA=0 ! PLY 1 bottom MAT=EL-MAT 1 THICK=0.5 THETA=90 ! PLY 2 || MAT=EL-MAT 1 THICK=0.5 THETA=90 ! PLY 3 \/ MAT=EL-MAT 1 THICK=0.5 THETA=0 ! PLY 4 top
Benchmarks
The main benchmark files in the Carat++-repository are
'../examples/benchmark_examples/elements/shell9composite_canti_temperature/cbm_SHELL9comp_temperature.dat'
'../examples/benchmark_examples/elements/shell9composite_canti_temperature_GLOB6/cbm_SHELL9comp_temperature.dat'
'../examples/benchmark_examples/elements/shell9composite_globrot_nln/cbm_SHELL9_NLN.dat'
'../examples/benchmark_examples/elements/shell9composite_globrot_tensile/cbm_TENSILE_SHELL9.dat'
'../examples/benchmark_examples/elements/shell9composite_squareplate_ortho/cbm_shell9comp_plate.dat'
'../examples/benchmark_examples/elements/shell9composite_stress_nln/cbm_shell9comp_plate.dat'
'../examples/benchmark_examples/elements/shell9_GlobRot_moment_load/cbm_shell9_momentload.dat'
'../examples/benchmark_examples/elements/shell9_nln_composite/cbm_composite_nln.dat'
Known Issues
Eigenvalue analysis with DIR_DIFF gives wrong results (AE, SSH;2017)
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