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高超声速飞行器飞行时会引起气动加热,对其进行结构动力学分析时需考虑气动热的影响。文中建立了热环境下的结构动力学分析流程。首先,基于求解三维可压缩N-S方程的CFD方法进行气动热分析;然后利用有限单元法(FEM)求解结构热传导,并得出温度场分布;最后,基于准线性结构模型进行热环境下的结构动力学分析。基于该流程,对比分析了高超声速飞行器复合材料翼面的结构动力学特性。结果表明,气动加热改变了翼面的固有振动特性。
Hypersonic aircraft can cause aerodynamic heating during flight, and the aerodynamic heat effects need to be considered when performing structural dynamics analysis. In this paper, the structural dynamics analysis process in thermal environment is established. First, CFD method based on solving three-dimensional compressible Navier-Stokes equations is used to conduct aerodynamic analysis. Then finite element method (FEM) is used to solve the structural heat conduction and obtain the temperature field distribution. Finally, based on the quasi-linear structure model, Analysis. Based on this process, the structural dynamic characteristics of the composite aerofoil of a hypersonic vehicle are compared and analyzed. The results show that the aerodynamic heating changes the natural vibration characteristics of the airfoil.