论文部分内容阅读
对复合材料的弹翼结构进行热效应分析．利用超音速热空气动力学理论，对六角形翼型的弹翼进行了气动加热计算；用一维有限元模型对弹翼结构进行了非线性、瞬态温度场计算，其中考虑了材料热传导系数随温度变化的相关性，以及气动加热系数与幅射边界条件的非线性；利用温度场结果，采用高阶有限板元模型对弹翼的热应力和变形进行了计算分析．计算结果表明，与已有结果吻口较好．此分析模型和程序可用来进行复合材料弹翼的结构设计
The thermal effect analysis of the composite wing structure. Based on the supersonic thermo-aerodynamics theory, the airfoil of the hexagonal airfoil is aerodynamically heated. The nonlinear and transient temperature field of the airfoil is calculated by the one-dimensional finite element model. The heat transfer coefficient The correlation with the temperature and the nonlinearity of the aerodynamic heating coefficient and the radiation boundary conditions. The thermal stress and deformation of the missile wing are calculated and analyzed by using the high-order finite plate element model. The calculation results show that it is better to kiss the existing results. This analytical model and procedure can be used to structure the composite wing