No abstract

No abstract

No abstract

Closed-form approximate solutions for uniaxial and biaxial compressive buckling of rectangular symmetric angle-ply laminates are developed from eigensensitivity analysis. Boundary conditions, which consist of the various combinations of clamped and simply supported edges, are incorporated through appropriate edge condition parameters. Calculated results, presented for elastic moduli ratios up to 40, compare quite favorably with the corresponding buckling loads obtained from the Ritz method.rectangular plate in x and y directions = eigenvector = matrices defining the boundary conditions where x is defined as constant = matrices defining the boundary conditions where y is defined as constant = bending stiffnesses of composite laminate = unit vector whose only nonzero component is the (w,n)th component = self adjoint operators= symmetric matrices equivalent to E, M operators, respectively = elements of the [K] and [M] matrices = diagonal matrices obtained by setting the off-diagonal elements of [K] and [M] equal to zero = zero-diagonal matrices obtained by setting the diagonal elements of [K] and [M]equal to zero = normalized Ritz critical buckling load = normalized approximate buckling load = in-plane stress resultants = transformation matrix = plate's aspect ratio a/b = dummy parameters = mutually adjoint differential operators = normalized beam shape functions on (0,1) = eigenfunction = invariant material property = transverse deflection = (m, n)th component of the eigenvector a/ 7 -= ratio of in-plane stress resultants N y /N x = laminate ply angle with respect to the x axis = eigenvalue corresponding to eigenfunction = beam's frequencies corresponding to X p andK

No abstract