摘要
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。
To investigate the temperature, stress and strain condition of missile case flying at certain altitude, and examine the structural strength of case, the aerodynamic heating computational method of missile case was studied. Aerodynamic heating boundary condition was simplified, and the 3D finite element model was established to compute the temperature changes of case along with the missile flight time. The computa- tional results agree well with the wind tunnel test results. The coupling thermo-meehauical computation method in ABAQUS was analyzed, external loads were exerted to this model according to different time,and the coupling thermo-mechanical numerical analysis was realized. The coupled thermo-mechanical loading test was carried out. The computational results agreed well with the test results. Both strain and stress are smaller than the ultimate value. This finite element computational method may be applied to the coupling thermo-mechanical intensity analysis of the case in Solid Rocket Motor.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2013年第1期109-114,共6页
Journal of Propulsion Technology
关键词
固体发动机
强度
热力耦合
气动加热
Solid rocket motor
Intensity
Coupling thermo-mechanical
Aerodynamic heating
