%% 1. Material Properties (Example: Carbon/Epoxy) E1 = 181e9; % Longitudinal Modulus (Pa) E2 = 10.3e9; % Transverse Modulus (Pa) G12 = 7.17e9; % Shear Modulus (Pa) nu12 = 0.28; % Poisson's Ratio
%% Visualization figure; surf(X, Y, reshape(w, size(X))); xlabel('x (m)'); ylabel('y (m)'); zlabel('w (m)'); title('Transverse deflection of composite plate'); colorbar; axis equal;
are the reduced stiffness components derived from engineering constants ( 2.2. Laminate Level (Force-Deformation) The overall bending behavior is captured by the matrix (Extensional, Coupling, and Bending stiffness): Composite Plate Bending Analysis With Matlab Code
Compute global strains at any specific layer depth
) using numerical methods like the .
[ (A_ij, B_ij, D_ij) = \sum_k=1^N \int_z_k-1^z_k \barQ_ij^(k) (1, z, z^2) , dz, \quad i,j=1,2,6, ]
q(x,y)=∑m=1∞∑n=1∞Qmnsin(mπxa)sin(nπyb)q open paren x comma y close paren equals sum from m equals 1 to infinity of sum from n equals 1 to infinity of cap Q sub m n end-sub sine open paren the fraction with numerator m pi x and denominator a end-fraction close paren sine open paren the fraction with numerator n pi y and denominator b end-fraction close paren D_ij) = \sum_k=1^N \int_z_k-1^z_k \barQ_ij^(k) (1
The first step is determining the , which relates mid-plane strains and curvatures to applied resultants (forces and moments). Determine Reduced Stiffness ( ): Calculate the matrix for each layer using its material properties ( Transform Stiffness (
% Compute ABD and As [ABD, As] = laminate_ABD(plies, z_coords, mat_props); As] = laminate_ABD(plies