The in-plane stiffness of honeycomb structures is several orders of magnitude lower than the material itself, making them an ideal sandwich structure for flexible deformation mechanisms of high-speed aircrafts in a high-temperature environment. Finite element method is widely used to simulate the in-and-out-of-plane large deformation of honeycomb structures; however the high computational cost is still a major bottleneck for fast analysis and optimization design. The existing reduced-order methods are mainly applicable to buckling problems, rather than the in-plane and out-of-plane large deformation case of honeycomb structures. In this work, a geometrically nonlinear reduced-order method considering both the thermal expansion and temperature-dependent material properties is proposed for in-and-out-of-plane large deformation analysis of honeycomb structures subjected to a high temperature field. The dual reduced-order models with only one degree of freedom are constructed for the temperature rise and mechanical loading phases, respectively, based on the third-order equilibrium equations and perturbation method. The constructional efficiency of the reduced system is largely improved by zeroing the fourth-order strain energy variation using the two-field Hellinger-Reissner variational principle and three-dimensional (3D) solid element. The nonlinear predictor solved by the reduced-order model can be corrected when its numerical accuracy is not satisfactory in path-following analysis. Various numerical examples demonstrate that the proposed method has a superior path-following capability for 3D finite element analysis of honeycomb structures.
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