空空导弹敏捷转弯反作用喷气控制研究  

Agile turn control considerations for air-to-air missile with reaction jets control system

作　　者：王鹏[1] 陈万春[1] 邹晖[1] 殷兴良[2] 

机构地区：[1]北京航空航天大学宇航学院,北京100083 [2]中国航天科工集团长峰机电技术设计研究院,北京100830

出　　处：《北京航空航天大学学报》2004年第5期395-399,共5页Journal of Beijing University of Aeronautics and Astronautics

基　　金：航空科学基金资助项目 ( 99D 51 1 1 4)

摘　　要：为了提高近距空空导弹离轴发射和攻击载机后半球目标的能力 ,在俯仰平面内研究了使用反作用喷气控制空空导弹敏捷转弯的问题 .为了实现导弹的敏捷转弯 ,提出了通过控制导弹姿态来控制导弹速度方向的方法 ,从理论上证明了该方法的可行性 .考虑到反作用喷气输入的开关特性 ,使用滑动模态方法设计了导弹的姿态控制系统 ,滑动模态可达的一个充分条件为反作用喷气提供的可控力矩不小于导弹的最大气动俯仰力矩 .反馈增益可以通过非线性仿真或者优化来选择 .非线性仿真的结果再次表明本文提出的转弯方法的可行性 。The control problem of the air to air missile during the agile turn phase was investigated using the reaction jets control system, which can increase the off borsight capability of short range air to air missile and the capability of intercepting the rear hemispherical target. A method was proposed to control the orientation of the missile velocity by controlling the attitude of the missile, and this method proved feasible in theory. Considering the on off property of the reaction jets control system, the sliding mode control method is used for attitude control. A sufficient condition for the reachability of the sliding mode is that the moment provided by the reaction jets control system should be no less than the maximum aerodynamical pitch moment. The feedback gain can be selected by nonlinear simulation or optimization. The results of nonlinear simulation showed once again the feasibility of the agile turn method proposed here. The sliding mode attitude control method also prove effective according to the results.

关 键 词：空对空导弹 导弹控制 姿态控制 开关控制 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]