垂发冷弹射导弹四推冲器转弯动力学研究  

Dynamics Research for a Vertical Soft Launched Missile with Four Rocket Pulse Engines

作　　者：孙晓峰 李毅 郭一达 SUN Xiaofeng;LI Yi;GUO Yida(Navigation Guidance and Control Institute of NORINCO Group,Beijing 100089,China)

机构地区：[1]中国兵器工业导航与控制技术研究所,北京100089

出　　处：《现代防御技术》2024年第2期22-32,共11页Modern Defence Technology

摘　　要：针对四推冲器转弯控制技术与其他垂发冷弹射导弹转弯控制技术存在较大差异的问题,建立了导弹的转弯段线运动方程、姿态运动方程和待转信息方程;设计了转弯时序,通过引入预估模型及相应判据设计了转弯控制策略;并基于上述策略开展了参数匹配研究;通过简易装置实现了弹体轴线的大范围调节。通过仿真算例验证了所提出参数匹配关系以及转弯控制策略的有效性。There is a big difference between the turning control technology for four rocket pulse engines and other turning control technologies for vertical soft launched missiles.In view of this problem,the turning segment line motion equation,the attitude motion equation,and the turning information equation of the missile were established in this paper.The turning time sequence was designed,and a turning control strategy was designed by introducing the prediction model and the corresponding criterion.Based on the strategy,the parameter matching research was carried out.Finally,a large range of adjustment of the missile axis was realized by a simple device.A simulation example was given to verify the effectiveness of the proposed parameter matching relationship and the turning control strategy.

关 键 词：垂直发射 冷弹射导弹 动力学研究 推冲器 简易控制 转弯控制 转弯策略 

分 类 号：TJ760.11[兵器科学与技术—武器系统与运用工程]