Composite Materials
The properties of the two orthotropic materials used in this problem are summarized in the tables below. They are assumed to be linear elastic and temperature independent. These materials are used to define the layers of the composite materials that make up the skin, stringer flange, and stringer web (refer to the shell section definitions later in this section).
| Linear Elastic Material Number 1 | |
|---|---|
| Young's Modulus in X direction (MPa) | 130000 |
| Young's Modulus in Y direction (MPa) | 8000 |
| Young's Modulus in Z direction (MPa) | 8000 |
| Poisson's Ratio (PRXY, PRYZ, PRXZ) | 0.3 |
| Shear Modulus GXY (MPa) | 5000 |
| Shear Modulus GYZ (MPa) | 2500 |
| Shear Modulus GXZ (MPa) | 5000 |
| Linear Elastic Material Number 2 | |
|---|---|
| Young's Modulus in X direction (MPa) | 68918 |
| Young's Modulus in Y direction (MPa) | 68918 |
| Young's Modulus in Z direction (MPa) | 4000 |
| Poisson's Ratio (PRXY, PRYZ, PRXZ) | 0.31 |
| Shear Modulus GXY (MPa) | 4000 |
| Shear Modulus GYZ (MPa) | 3250 |
| Shear Modulus GXZ (MPa) | 3250 |
Cohesive Zone Model
The properties of the bilinear cohesive zone material model with the CBDE option are summarized in the table below. The TB and TBDATA commands are used to define this material model. See Cohesive Zone Material for Contact Elements in the Material Reference for details on the definition of cohesive zone models.
| Cohesive Zone Model Properties | |
|---|---|
| Maximum normal contact stress (σmax) | 61 |
| Critical fracture energy for normal separation (Gcn) | 0.075 |
| Maximum equivalent tangential contact stress (τmax) | 68 |
| Critical fracture energy for tangential slip (Gct) | 0.6 |
| Artificial damping coefficient (η) | 5.e-4 |
| Flag for tangential slip under compressive normal contact stress (β) | 1 |
Shell sections are used for defining the layup of the composite materials. See the SECTYPE and SECDATA commands for details on how to define the material, thickness, material orientation, and the number of integration points of each layer. The following tables summarize the section properties for the skin, the flange, and the web.
| Section Properties for Skin | |||
|---|---|---|---|
| Layer Thickness | Material | Orientation Angle from local x direction | Integration Points |
| 0.14 | 1 | 45 | 3 |
| 0.14 | 1 | -45 | 3 |
| 0.14 | 1 | 45 | 3 |
| 0.14 | 1 | -45 | 3 |
| 0.14 | 1 | 45 | 3 |
| 0.14 | 1 | -45 | 3 |
| 0.14 | 1 | 0 | 3 |
| 0.14 | 1 | 0 | 3 |
| 0.14 | 1 | -45 | 3 |
| 0.14 | 1 | 45 | 3 |
| 0.14 | 1 | -45 | 3 |
| 0.14 | 1 | 45 | 3 |
| 0.14 | 1 | -45 | 3 |
| 0.14 | 1 | 45 | 3 |
| Section Properties for Stringer Flange | |||
|---|---|---|---|
| Layer Thickness | Material | Orientation Angle from local x direction | Integration Points |
| 0.36 | 2 | 45 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.36 | 2 | 45 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.36 | 2 | 45 | 3 |
| Section Properties for Stringer Web | |||
|---|---|---|---|
| Layer Thickness | Material | Orientation Angle from Local x Direction | Integration Points |
| 0.36 | 2 | 45 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.36 | 2 | 45 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.36 | 2 | 45 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.36 | 2 | 45 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.36 | 2 | 45 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.125 | 1 | 0 | 3 |
| 0.36 | 2 | 45 | 3 |