曲率半径对前缘气动热与结构响应的影响

摘要

针对高超声速飞行器铌合金前缘结构,研究了不同曲率半径对前缘结构温度场、应力场和变形场的影响.首先建立高超声速气动加热模型,采用有限体积法得到热环境参数,并运用有限元法计算结构的温度、应力和变形.结果表明:不同时间的温度场分布和曲率半径密切相关,温升过程中应力最大值出现在曲率半径为1 mm时;随时间推移,曲率半径越大应力越低;而位移随曲率半径的增加而增大.%Influences of the curvature radius of the hypersonic leading edge on the evolution of temperature,stress, and deformation are studied in this paper.Firstly, the hypersonic aerodynamic heating model is established to determine the thermal environment of the leading edge made of niobium alloy by the finite volume method.Secondly, the temperature field, stress field, and deformation field of the leading edge with their evolution are obtained by the finite element method.The numerical results reveal that the evolution of the temperature field is closely related to the curvature radius.The stress value of the leading edge during the aerodynamic heating process reaches the maximum when the curvature radius is i mm; the displacement increases with the increase of the curvature radius.