空空导弹大角度姿态推力矢量控制研究  

Large angle attitude thrust vector control for an air-to-air missile

作　　者：王鹏[1] 陈万春[1] 殷兴良[2] 

机构地区：[1]北京航空航天大学宇航学院504教研室,北京100083 [2]中国航天科工集团第二研究院,北京100830

出　　处：《宇航学报》2004年第3期295-299,共5页Journal of Astronautics

基　　金：航空科学基金资助项目(99D51114)

摘　　要：为研究具有大离轴角及越肩发射能力的先进空空导弹敏捷转弯方法,研究了空空导弹的大角度姿态机动控制律。利用时间尺度分离的方法将导弹的姿态动力学和运动学系统分别看做快子系统和慢子系统。用李亚普诺夫方法设计了慢子系统控制律。利用动态逆方法设计了快子系统控制律。分析了控制系统的鲁棒性和稳态精度。仿真结果证明了所提控制方法能够大大减小空空导弹大角度姿态机动时各种力矩干扰的影响。最后给出了采用姿态控制实现的越肩发射的仿真结果。Large angle attitude control law is investigated for agile turn of an advanced air-to-air missile that has high off-boresight or over the shoulder capability. The attitude dynamics and kinematics of the missile are divided into fast subsystem and slow subsystem by time scale separation. The fast subsystem control law is designed by dynamic inversion. The slow subsystem control law is designed by Lyapunov method. The robustness and precision of the system are analyzed. The simulation shows that the effect of the moment disturbance is highly reduced with the control law proposed here. The simulation result of the agile turn of the over the shoulder mission realized by attitude control method was also given as the application of the control law proposed here.

关 键 词：空空导弹 大角度姿态机动 推力矢量控制 

分 类 号：V448[航空宇航科学与技术—飞行器设计]