载机大机动条件下空空导弹弹射发射动力学研究

摘要

大机动条件下实现空空导弹的内埋弹射发射是隐身战机的重要作战性能,在大机动条件下弹射发射空空导弹,导弹弹射分离参数将偏离设计值,严重威胁隐身战机发射安全.基于多柔体动力学拉格朗日乘子法、构件级模态试验和载机大机动条件,提出了一种隐身战机大机动内埋弹射刚-柔-液耦合的动力学建模方法,并通过数值模型仿真了相关发射动力学特性,分析了载机大机动产生的高过载离心力对空空导弹的弹射分离参数的影响.结果表明大机动弹射发射将使弹射分离姿态角明显减小,威胁发射安全性.为隐身战机大机动发射安全性研究和空空导弹初始弹道研究提供理论依据.%It's an important operational performance of stealth aircrafts to realize embedded ejection and launch of air-to-air missiles under the condition of carriers' large maneuvering flight.Carriers' large maneuvering flight makes missile ejection separation parameters deviate design values to threat seriously the launch safety of stealth aircrafts.Based on the flexible multi-body Lagrange multiplier method,components modal tests and the condition of stealth aircrafts' large maneuvering flight,a rigid-flexible-liquid coupled dynamic modeling method for stealth aircrafts' embedded ejection under their large maneuvering flight was put forward.The corresponding launch dynamic characteristics were simulated.The influences of high overload centrifugal force produced due to carriers' large maneuvering flight on the ejection separation parameters of air-to-air missiles were analyzed.The simulation results showed that carriers' large maneuvering flight makes missiles' ejection separation attitude angle decrease obviously to threat missiles' launch safety.The results provided a theoretical basis for further studying stealth aircrafts' launch safety under large maneuvering flight and initial trajectories of air-to-air missiles.