复合材料弹翼结构热力力学分析

THERMOMECHANICAL ANALYSIS IN COMPOSITE WINGS OF GUIDED MISSILE

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．

Thermal stresses arising in a supersonic missile wing structure must be taken into account in the design of the composite wings.A simple description of the aeroheating calculation of the wing by using Eckert's referential temperature method and 2 D supersonic flow theory,transient thermal analysis by using 1 D finite element model accounting the nonlinearities of material and boundary conditions and an analysis of thermal stresses and deflections by using higher precision triangular plate element were made.The calculation results show the methods and the codes presented are suitable for the preliminary design of composite wings.