% Calculate nu21 using reciprocity relation nu21 = nu12 * (E2/E1); Bokeh 2.3.3 Apr 2026
%% 3. Calculate Reduced Stiffness Matrix [Q] for 0-degree ply % Using Plane Stress assumption Q11 = E1 / (1 - nu12*nu21); Q22 = E2 / (1 - nu12*nu21); Q12 = (nu12 * E2) / (1 - nu12*nu21); Q66 = G12; Veer Zaara Movie Download Filmyzilla.com Apr 2026
% Position of ply interfaces (z-coordinates) z_bot = -total_thickness/2; z = zeros(n_plies+1, 1); for i = 1:n_plies+1 z(i) = z_bot + (i-1)*h; end
%% 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
%% 6. Display ABD Matrix disp('Extensional Stiffness [A] (N/m):'); disp(A); disp('Coupling Stiffness [B] (N):'); disp(B); disp('Bending Stiffness [D] (N-m):'); disp(D);
% If symmetric laminate (B=0), we can solve simply for curvatures: % M = D * k => k = D_inv * M
A simplified engineering approximation for the central deflection $w_{max}$ of a rectangular plate ($a \times b$) is: