针对火箭弹飞行过程中的尾翼展开强度问题,以某火箭弹尾翼为对象,通过尾翼展开过程的理论分析,建立了尾翼展开分析模型,分析了尾翼展开过程中展开角和转速随时间的变化关系以及所受外载荷情况。基于分析所得载荷条件,采用数值模拟方式分析了两种不同结构尾翼展开过程中与尾翼座形成冲击时的应力响应情况。通过外弹道飞行试验对分析结果进行了验证。结果表明,分析结果与试验结果具有较好的一致性。

In view of spread strength of empennage during rocket flight, as the object on a rocket empennage, the analytical model of empennage spread was established on the theoretical analysis of empennage spread process. The relationship between spread angle and rotate speed of empennage with time during empennage spread process were obtained from the model, and the load condition of empennage was also obtained. Based on the load condition from the analysis results, the stress responses of two different-structure empennages impacting on empennage seat when deploying were analyzed by numerical simulation. The analytical results were validated by exterior ballistic flight test. As a result, the results of analysis show good agreement with the test results.