Supersonic LCO responses of composite panels with consideration of transient aerodynamic heating effect
LIU Yating1， DUAN Jingbo1,2， XU Buqing1,2， GAO Yihang3,4
1.Department of Engineering Mechanics, Shijiazhuang Tiedao University, Shijiazhuang 050043,China;
2.Hebei Research Center of the Basic Discipline Engineering Mechanics, Shijiazhuang Tiedao University, Shijiazhuang 050043,China;
3.College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073,China;
4.Beijing Institute of Astronautical Systems Engineering, Beijing 100076,China
Abstract：The nonlinear aerothermoelastic behavior of composite panels with transient aerodynamic heating temperature effect was investigated. For the aerothermal model, the aerodynamic heat flux was obtained using the Eckert reference temperature method and the two-dimensional transient temperature field including the in-plane and through-thickness directions of the panel was calculated by the finite difference method. For the aeroelastic model, the Von Karman assumption was used to describe the large-deflection deformation of the composite wall plate, and the first-order piston theory was used to calculate the supersonic aerodynamic force. After the verification of the proposed method, the transient temperature response and aeroelastic limit cycle oscillation (LCO) response of composite panels considering the transient effect of aerodynamic heating were first presented, and compared with the aeroelastic LCO response of the panel in the steady-state temperature field. Moreover, the influences of the shock wave, incoming flow pressure, heat transfer coefficient and initial interference force on the supersonic aerothermoelastic LCO response and transient temperature field of composite panels considering the transient aerodynamic heating temperature effect were discussed.
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