带落角约束的自适应比例制导律  

Adaptive proportional navigation with terminal angular constraint

作　　者：张旭[1] 雷虎民[1] 曾华[1] 肖增博[1] 叶继坤 

机构地区：[1]空军工程大学导弹学院,三原713800

出　　处：《固体火箭技术》2011年第6期687-692,共6页Journal of Solid Rocket Technology

基　　金：航空科学基金(20090196005;20100196002)

摘　　要：为使导弹能够以一定的落角约束有效命中机动目标,构造了带有落角约束的导弹运动学方程,并设计了自由切换导航系数的自适应比例制导律。通过对弹目运动学模型和角度约束几何关系进行详细推导,得出导航系数的自适应调整函数,形成了基于导弹运动学模型的带有反馈形式的自适应比例制导策略,并证明了所给制导律既能够满足命中目标的要求,又可实现全向攻击;考虑导弹的实际模型,对制导律进行修正,得到了基于实际模型的自适应比例制导律。为体现所给制导律的基本性能和实际应用价值,分别针对导弹空-地作战和地-地作战进行仿真分析。仿真结果表明,所设计的制导律制导性能良好,具有一定的工程应用价值。A missile motion equation with terminal angular constraint was derived and then adaptive proportional guidance laws adopting adaptive navigation constant were designed to realize effective interception of maneuvering target with certain terminal angular constraint. That is through particular derivation of missile-target motion model and the geometry relationships of angular constraint, an adaptive adjustable function was derived and then the adaptive proportional guidance law based on missile kinematics was formed with feedback form. It is proven that the proposed guidance law could meet the requirements of successful interception with arbitrary attack angle. Another adaptive proportional guidance law based on realistic model was derived after revising the previous law. Simulations were made for air-to-ground and ground-to-ground missiles in order to display the fundamental advantages and practical values. Simulation results show that the proposed guidance laws have better guidance effect and could offer some references for engineering application.

关 键 词：导弹 落角约束 机动目标 自适应比例导引 

分 类 号：V448[航空宇航科学与技术—飞行器设计]