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AEROTHERMOELASTIC ANALYSIS OF HYBRID COMPOSITE LAMINATES WITH TWO NON-UNIFORMLY DISTRIBUTED FIBERS
摘要
This study presents the first-known flutter analysis of thermally post-buckled hybrid composite laminates with non-uniformly distributed graphite and E-glass fibers in a single lamina. A 54 degree-of-freedom high order triangular plate element is developed based on the Von Karman large deflection assumption and quasi-steady supersonic aerodynamic theory. The formulations of the location dependent linear stiffness matrix, nonlinear stiffness matrix, and consistent mass matrix due to non-homogeneous material properties, geometrical stiffness matrix due to thermal effects, thermal moment vector due to temperature gradient, and aerodynamic matrix are derived. The effects of fiber distribution on aerothermoelastic behavior of hybrid composite laminates subjected to aerodynamic force and thermal stress are studied in the frequency and time domains. The numerical results reveal that the redistribution of two fibers can considerably increase the flutter boundary of hybrid composite laminates. Special flutter mode shapes and flutter boundary are observed, along with the ＂local flutter＂ and ＂flutter mode shifting＂ phenomena.
延伸閱讀
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