Here is a simplified script to calculate the bending stiffness (D matrix) of a symmetric laminate: % Material Properties (e.g., Carbon/Epoxy) ; v21 = v12 * E2 / E1; % Reduced Stiffness Matrix [Q] -v12*v21), v12*E2/( -v12*v21), ; v12*E2/( -v12*v21), E2/( -v12*v21), % Layup: [0/45/-45/90]s ]; t_ply = % thickness of each ply n = length(theta); h = n * t_ply; z = -h/ : t_ply : h/ % z-coordinates of interfaces D = zeros(
%% 5. LOAD VECTOR (Uniform pressure) % Pressure acts as transverse load (w direction) for e = 1:nelem nodes_e = ien(e,:); xe = nodes(nodes_e, 1); ye = nodes(nodes_e, 2); % Element length and width Le = max(xe) - min(xe); We = max(ye) - min(ye); % Equivalent nodal forces (for 4-node, simply distribute) Pe = q0 * Le * We / 4; for i = 1:4 dof_idx = (nodes_e(i)-1)*ndof + 3; % w DOF F_global(dof_idx) = F_global(dof_idx) + Pe; end end Composite Plate Bending Analysis With Matlab Code
%% 2. Mesh Generation [X, Y, nodeCoords, elements] = mesh_rectangular(a, b, nx, ny); nNodes = size(nodeCoords,1); nElem = size(elements,1); ndof = 5; % DOF per node: w, theta_x, theta_y nDofs = nNodes * ndof; Here is a simplified script to calculate the
For a laminate with N layers, the (3×3) is defined as: % Reduced Stiffness Matrix [Q] -v12*v21)