一种用于反攻击型无人飞行器的导弹末制导律  

A Terminal Guidance Law for Missile Against the Attacking Unmanned Aerial Vehicles

作　　者：江秀强[1] 

机构地区：[1]南京航空航天大学航天学院,江苏南京210016

出　　处：《战术导弹技术》2013年第1期87-92,共6页Tactical Missile Technology

摘　　要：以反攻击型无人飞行器(AUAV)为工程应用背景。首先,基于导弹与AUAV类目标的非线性相对运动关系模型,给出了导弹的滑模变结构制导。然后,建立了模糊神经网络模型,利用模糊神经网络调整了引起抖振的参数,进一步削弱了滑模变结构制导律中存在的抖振。仿真结果表明:当AUAV作复杂大机动逃逸时,智能制导律能够以较短的时间和较小的指令加速度取得更小的脱靶量,与滑模变结构制导相比该制导律有较大的性能改善。To against the attacking unmanned aerial vehicles （AUAV）, based on the nonlinear model of relative movement between missile and AUAV, sliding mode variable structure guidance law is presented. Then, fuzzy neural network model is built, and the buffeting in sliding mode variable structure guidance law is further weakened by adjusting the parameters which lead to buffeting. The simulation results show that in the states of AUAV escaping by intricately and highly maneuver, this intelligent guidance law can get a smaller miss distance through shorter time and smaller command acceleration, performance has been improved greatly than the sliding mode variable structure guidance law.

关 键 词：攻击型无人飞行器 滑模变结构制导 末制导 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程] V448.12[航空宇航科学与技术—飞行器设计]