end
%% 2. MATERIAL AND LAMINATE STIFFNESS CALCULATION % Compute reduced stiffness for a lamina (plane stress) Q11 = E1/(1 - nu12^2*(E2/E1)); Q12 = nu12 E2/(1 - nu12^2 (E2/E1)); Q22 = E2/(1 - nu12^2*(E2/E1)); Q66 = G12; Composite Plate Bending Analysis With Matlab Code
% Node numbering: global DOF = 3*(node_index - 1) + dof (1:w, 2:theta_x, 3:theta_y) n_nodes = nx * ny; n_dof = 3 * n_nodes; end %% 2
clear; clc; close all;
% Element connectivity (4-node rectangular element) ien = zeros(nelem, 4); for j = 1:ny for i = 1:nx e = (j-1) nx + i; n1 = (j-1) (nx+1) + i; n2 = n1 + 1; n3 = n2 + (nx+1); n4 = n3 - 1; ien(e,:) = [n1, n2, n3, n4]; end end Q22 = E2/(1 - nu12^2*(E2/E1))
% Stresses and strains stresses = zeros(3,1); strains = zeros(3,1); for i = 1:length(t) zi = z(i); stresses = [Q11, Q12, Q16; Q12, Q22, Q26; Q16, Q26, Q66] * (ex0 + zi * kx); strains = [ex0 + zi * kx; ey0 + zi * ky; gxy0 + zi * kxy]; end
The code uses typical Carbon Fiber Reinforced Polymer (CFRP) properties.
