机载导弹大机动弹射发射动力学特性分析

先进战机在大机动条件下需要实现导弹的内埋式弹射发射,战机大机动发射时导弹弹射分离参数偏离理想设计值,威胁导弹与载机的分离安全。采用理论仿真和试验相结合的方法对战机大机动下的导弹发射动力学进行研究。基于有限元法和柔性多体系统拉格朗日动力学方程并考虑发射系统刚柔气液耦合特性,建立了载机大机动条件性下的导弹弹射发射动力学模型,仿真分析了载机大机动时的离心力和科氏力对导弹弹射分离参数的影响。最后，通过发射试验进行了实际验证。仿真及试验结果表明:离心力有利于发射安全性,科氏力对发射安全性具有负面的影响,大机动发射时须考虑科氏力的影响。

Launch dynamics of airborne missile with large maneuvering flight

Advanced fighter needs to achieve embedded ejection of missile under large maneuvering flight, High overload centrifugal force and Coriolis effect has influences on launch dynamics, and harmful to the launch separation safety. research on launching safety of stealth aircraft was carried out that combines simulation and test. Based on finite element method and Lagrange multi body dynamic equation, launch dynamics theory model of embedded ejection of stealth aircraft was established, and launch dynamics was simulated. The influence of high overload centrifugal force and Coriolis force on the ejection separation parameter was analyzed. Simulation and test results show that high overload centrifugal force has positive influences on launch safety,but Coriolis force has negative influences on launch safety.