Supersonic LCO responses of composite panels with consideration of transient aerodynamic heating effect

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Journal of Vibration and Shock ›› 2024, Vol. 43 ›› Issue (2) : 315-322.

LIU Yating1， DUAN Jingbo1,2， XU Buqing1,2， GAO Yihang3,4

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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.

Key words

composite panel / supersonic flutter / transient heat conduction / aerodynamic heating

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LIU Yating1， DUAN Jingbo1,2， XU Buqing1,2， GAO Yihang3,4. Supersonic LCO responses of composite panels with consideration of transient aerodynamic heating effect[J]. Journal of Vibration and Shock, 2024, 43(2): 315-322

References

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