Composite Plate Bending Analysis With Matlab Code Now

%% Finite Difference Grid Nx = 41; Ny = 25; % odd numbers to include center dx = a/(Nx-1); dy = b/(Ny-1); x = linspace(0, a, Nx); y = linspace(0, b, Ny);

% Ply stacking [0/90/90/0] (symmetric) theta = [0, 90, 90, 0]; % degrees z = linspace(-h/2, h/2, num_plies+1); % ply interfaces

[ \frac{\partial^4 w}{\partial x^2 \partial y^2} \approx \frac{ w_{i-1,j-1} - 2w_{i-1,j} + w_{i-1,j+1} - 2w_{i,j-1} + 4w_{i,j} - 2w_{i,j+1} + w_{i+1,j-1} - 2w_{i+1,j} + w_{i+1,j+1} }{\Delta x^2 \Delta y^2} ] Composite Plate Bending Analysis With Matlab Code

%% Composite Plate Bending Analysis Using CLPT & Finite Differences clear; clc; close all; %% Material Properties (T300/5208) E1 = 181e9; % Pa E2 = 10.3e9; G12 = 7.17e9; nu12 = 0.28; nu21 = nu12 * E2/E1;

% Map 2D index to 1D idx = @(i,j) (j-1)*Nx + i; %% Finite Difference Grid Nx = 41; Ny

[ D_{11} \frac{\partial^4 w}{\partial x^4} + 2(D_{12}+2D_{66}) \frac{\partial^4 w}{\partial x^2 \partial y^2} + D_{22} \frac{\partial^4 w}{\partial y^4} = q(x,y) ]

Boundary conditions (simply supported): [ w = 0,\quad M_{xx}=0 \Rightarrow \frac{\partial^2 w}{\partial x^2}=0 \text{ on } x=0,a ] (same for y-direction) Ny = 25

% Reduced stiffness matrix (plane stress) Q11 = E1/(1-nu12 nu21); Q12 = nu12 E2/(1-nu12 nu21); Q22 = E2/(1-nu12 nu21); Q66 = G12;