The core of composite analysis is the , which relates the in-plane force resultants ( ) and moment resultants ( ) to the mid-plane strains ( ϵ0epsilon sub 0 ) and curvatures (
A helpful MATLAB code should produce:
Where $\alpha$ depends on the aspect ratio $b/a$ and $D_11$ is the first term of the bending stiffness matrix. The MATLAB code provides you with the $D_11$ value required for this calculation. Composite Plate Bending Analysis With Matlab Code
The reduced stiffness matrix $[Q]$ relates stress and strain: $$ \beginBmatrix \sigma_1 \ \sigma_2 \ \tau_12 \endBmatrix = [Q] \beginBmatrix \epsilon_1 \ \epsilon_2 \ \gamma_12 \endBmatrix $$ The core of composite analysis is the ,
Given the applied moments (e.g., from a distributed load), solve the simultaneous equations to find from a distributed load)