机载固体火箭发动机壳体吊耳加强结构强度计算与试验研究

摘要

A finite element model was established for a shell lug strengthening structure of airborne solid rocket motor, and the strength calculation and analysis was done under one inclement flying load, at the same time, the static test of the solid rocket motor was carried out under the same load, then the feasibility of the finite element model was verified by the comparison between the results of finite element calculation and static test. Finally, the stress distribution of the lug strengthening structure was calculated under the other inclement flying load. It was proved that the reliability of the structure under the condition of airborne was demonstrated.%针对某挂机用固体火箭发动机壳体吊耳加强结构，建立吊耳加强结构的有限元计算模型，在某严酷挂飞载荷条件下进行强度计算与分析，并开展了相应载荷下的发动机整机静力试验，通过有限元计算结果与静力试验结果的对比研究，验证了计算模型的可行性。最后，计算了另一严酷载荷下该结构的应力分布，论证了吊耳加强结构在机载条件下工作的可靠性。