Composite Plate Bending Analysis With Matlab Code !!top!! 📍
% Element stiffness contribution Ke = Ke + B' * D * B * detJ * a_elem * b_elem * wxi * wet;
fprintf('Layer %d (%.0f deg):\n', k, layers(k)); fprintf(' Top (z=%.4f): Sx=%.2f MPa\n', z_top_k, stress_top(1)/1e6); end Composite Plate Bending Analysis With Matlab Code
if max(max(abs(B))) < 1e-10 disp('Laminate is Symmetric (B matrix is zero).'); D_inv = inv(D); kappa = D_inv * M_applied; % Curvatures [kx, ky, kxy] else disp('Laminate is Non-Symmetric. Solving full system.'); % Need to assume Nx, Ny, Nxy = 0 for pure bending N_applied = [0;0;0]; loads = [N_applied; M_applied]; ABD = [A, B; B, D]; strains_curvatures = inv(ABD) * loads; epsilon_0 = strains_curvatures(1:3); % Mid-plane strains kappa = strains_curvatures(4:6); % Curvatures end % Element stiffness contribution Ke = Ke +
%% 2. Laminate Definition % Stack sequence: [0/90/0] (Symmetric) layers = [0, 90, 0]; % Fiber angles in degrees total_thickness = 0.002; % Total thickness in meters (2mm) n_plies = length(layers); h = total_thickness / n_plies; % Thickness of single ply fprintf('Layer %d (%.0f deg):\n'
