%% 5. Assemble Global Matrices K_global = sparse(n_dof, n_dof); F_global = zeros(n_dof, 1);
f_e = ∫_-1^1∫_-1^1 p * [N_w]^T * det(J) * (a*b) dξ dη Only the w DOF has load; θx, θy loads are zero. The code below solves a simply supported square composite laminate [0/90/90/0] under uniform pressure. We compare center deflection with analytical series solution. 3.1 Complete MATLAB Code % ============================================================ % Composite Plate Bending Analysis using 4-node Rectangular Element % Classical Laminated Plate Theory (CLPT) % Degrees of freedom per node: w, theta_x, theta_y % ============================================================ clear; clc; close all; Composite Plate Bending Analysis With Matlab Code
% Dummy B (3x12) - replace with actual derivatives in real code B = zeros(3,12); % B matrix structure: row1: d2w/dx2, row2: d2w/dy2, row3: 2*d2w/dxdy % For actual implementation, please refer to standard FEA textbooks. We compare center deflection with analytical series solution
%% 4. Mesh Generation nx = Nx_elem + 1; ny = Ny_elem + 1; x_nodes = linspace(0, a, nx); y_nodes = linspace(0, b, ny); [X, Y] = meshgrid(x_nodes, y_nodes); Mesh Generation nx = Nx_elem + 1; ny