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为了研究导弹发动机壳体在高空飞行时的温度、应力、应变状态,从而对壳体的结构强度进行校核,研究了导弹壳体气动加热的计算方法,建立了某发动机壳体的三维有限元模型,合理简化气动边界条件,计算壳体温度随导弹飞行时间的变化。对比风洞试验结果,有限元计算结果与试验结果一致性较好。分析了ABAQUS软件热-力耦合实现方法,对该模型施加不同时刻的外力载荷,实现壳体的热-力耦合数值分析。进行热-力耦合联合加载试验,对比计算结果与试验结果,计算结果与试验结果吻合较好。壳体的应力、应变都远小于材料的极限值,壳体结构安全。该有限元计算方法可以用来进行壳体的热-力耦合强度分析。
In order to study the temperature, stress and strain state of the missile engine shell at high altitude, the structural strength of the shell is checked. The calculation method of the aerodynamic heating of the missile shell is studied. The three-dimensional finite element Model, reasonably simplify the aerodynamic boundary conditions, calculate the shell temperature with the missile flight time changes. Compared with the wind tunnel test results, the results of finite element analysis are in good agreement with the experimental results. The method of thermo-mechanical coupling in ABAQUS software is analyzed, and the external load at different time is applied to the model to realize the thermo-mechanical coupling numerical analysis of the shell. Thermal-mechanical coupled load test is carried out, and the calculated results and experimental results are compared. The calculated results are in good agreement with the experimental results. Shell stress, strain are far less than the material limit, the shell structure is safe. The finite element method can be used to analyze the thermal-mechanical coupling strength of the shell.