Consistent higher-order analysis on shock response of cross-ply curved panels

A consistent higher-order analysis is presented for the shock response of doubly-curved cross-ply laminated thick panels simply supported on four edges. Emphasis is laid on consistency with the three-dimensional boundary conditions and interlaminar stress continuity, respectively. In each layer, a three-dimensional dynamic displacement field is assumed in terms of in-plane double Fourier series and cubic polynomials in the thickness direction. A system of modified Lagrange equations is derived via an energy variational approach with all surface conditions, and interlaminar continuity included. Modal analysis is performed for the shock response using a modified exponential decay overpressure. Three-dimensional displacements and stresses can be found any time throughout the panels. Present results, including frequency spectra of σ33, are perfectly consistent with existing wave theory without prior assumption of wave motion.