utils.py
- openaerostruct.structures.utils.compute_composite_stiffness(surface)[source]
Function to compute the effective E and G stiffness values for a composite material, based on the ply_fractions, ply angles and individual fiber and matrix properties.
- Parameters:
- surfacedict
OpenAeroStruct surface dictionary.
- openaerostruct.structures.utils.compute_lamina_transformation_matrix(theta)[source]
Compute the stress and strain transformation matrices for a given ply angle.
This is the matrix $T$ that transforms stresses and strains from the global to the material coordinate system:
\[\begin{split}egin{bmatrix} \sigma_1 \\ \sigma_2 \\ au_{12} \end{bmatrix} = T egin{bmatrix} \sigma_x \\ \sigma_y \\ au_{xy} \end{bmatrix}\end{split}\]- Parameters:
- thetafloat
Angle in degrees.
- Returns:
- Tnumpy array
Transformation matrix.
- openaerostruct.structures.utils.radii(mesh, t_c=0.15)[source]
Obtain the radii of the FEM element based on local chord.