高速飞行器潜入式分离起控联合仿真方法研究  

A Co-simulation Method of Inserted Separation and Stabilization Controlfor Hypersonic Vehicle

作　　者：蒋希之 赵长见[1] 赵俊锋[1] 郭栋 JIANG Xizhi;ZHAO Changjian;ZHAO Junfeng;GUO Dong(China Academy of Launch Vehicle Technology,Beijing,100076)

机构地区：[1]中国运载火箭技术研究院,北京100076

出　　处：《导弹与航天运载技术（中英文）》2024年第5期16-20,27,共6页Missiles and Space Vehicles

摘　　要：高速飞行器需要在低空大动压的环境下实现与助推级的分离。目前基于极限偏差法的分离起控仿真预示不够真实,设计冗余大。对于长行程小间隙的潜入式分离,起控设计时无法对两级进行碰撞检测。针对以上问题,提出一种分离起控联合仿真预示方法,在上面级分离动力学模型中引入姿态控制模型,降低设计冗余度,提高精细化设计水平。其次,该方法能够实现分离、起控全过程的碰撞检测,为保证分离起控安全性提供支撑。该方法为上面级起控时间的选择提供了重要依据,对分离时序等的优化设计具有指导意义。The hypersonic vehicle needs to separate from the booster stage in an environment with low altitude and high dynamic pressure.The current prediction of separation and attitude control based on limit deviation method is not real enough and the design is heavily redundant.For inserted separation with long stroke and small gap,the collision detection of two stages cannot be carried out during the attitude control design process.To solve the above problems,a coupling calculating method of separation and attitude control is proposed,which introduces the attitude control model into separation dynamic model.Design redundancy is reduced and the level of refine is improved.Also,collision detection can be realized in the whole process,providing support for ensuring the safety of the separation and attitude control process.The method provides a basis for the time to start attitude control of the upper stage,and has guiding significance for optimization design of separation time sequence.

关 键 词：高速飞行器 级间分离 起控 联合仿真 多体动力学 

分 类 号：V448[航空宇航科学与技术—飞行器设计]