尾翼搭载固体火箭发动机壳体数值仿真及试验研究

摘要

A 3D finite element model was established for a special shell structure of tail mounted solid rocket motor, and the simulation on internal pressure and external load was carried out to direct the design about local structure of shell near the tail joints. In addition, the static test of the shell of tail mounted solid rocket motor was done under the same load, by the comparison between the results of finite element calculation and static test, the feasibility to guide the shell design by the finite element model was verified, and the simulation result was conservative slightly, by the way, the comparative deviation was 8.4%.%针对导弹尾翼搭载于固体火箭发动机壳体上这一特殊结构,建立3D有限元模型,进行内压与外载荷联合强度仿真计算,用于指导尾翼接头附近的壳体局部结构设计.并开展了相同载荷下尾翼搭载发动机壳体结构的静力试验,通过仿真计算及静力试验结果的对比,表明仿真计算可以指导尾翼搭载发动机壳体的结构设计,且仿真计算结果与静力试验结果偏差为8.4%.