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。

Aerodynamic heating would be caused when a hypersonic vehicle was in flight, so it should be taken into account when a structural dynamic analysis was carried out. A method for structural dynamic analysis in thermal environment was presented in this paper. Firstly, computational fluid dynamic (CFD) method based on solving the three-dimensional compressible Navier-Stokes (N-S) equations was employed to perform aerodynamic heating analysis. Secondly, finite element method (FEM) was used to solve structural heat conduction and get temperature distribution. Lastly, based on the quasilinear structural model, a structural dynamic analysis was analyzed in thermal environment. Based on the process, the structural dynamic characteristics of hypersonic composite wing were analyzed. The results indicated that the aerodynamic heating changed vibration characteristics of the wing.