Supersonic Flutter of a Honeycomb Sandwich Panel with Cermet Constrained Layer under Moving Load Configuration

In this paper, the effects of supersonic flutter and moving load are studied simultaneously on a honeycomb sandwich beam with a cermet covered layer. The core layer ratio is considered as a regular nomex honeycomb which has the high stiffness to weight ratio. Also cermet layer which has a high thermal strength is considered as aluminum oxide in mild steel matrix, for optimized fractional ceramic concentration. The structural formulation is based on the classical Euler-Bernoulli beam theory and the quasi-steady first order supersonic piston theory is employed to describe the aerodynamic loading. Hamilton’s principle in conjunction with the generalized Fourier expansions and Galerkin method are used to develop the dynamical model of the structural systems in the state-space domain. The critical dynamic pressures are obtained by p method for a honeycomb sandwich beam. Simulation results shows that using cermet layer as a constrained layer has an important role in postponding the flutter to higher dynamic pressures compared to the same sandwich layer with aluminum constrained layer. The thickness effect of cermet layer on flutter phenomena is also considered. Finally, in order to obtain efficeient operational results, the aeroelastic responses of honeycomb sandwich beam in supersonic regime under moving loads with different velocities are calculated.