带末端角度和速度约束的再入飞行器滑模变结构导引律  

A Sliding Mode Guidance Law for Reentry Vehicles with Impact Angle and Terminal Velocity Constraints

作　　者：谢道成 胡亚忠 张宏强 

机构地区：[1]第二炮兵驻8602厂军代表室,武汉430040

出　　处：《电光与控制》2014年第11期46-50,共5页Electronics Optics & Control

基　　金：国家自然科学基金(51105287)

摘　　要：在考虑末端角度和末端速度约束的前提下,研究滑模变结构导引律在再入飞行器上的应用。推导满足末端角度约束的滑模变结构导引律,给出俯冲平面和转弯平面的导引方程,依据导引方程生成需要攻角、侧滑角制导指令。设计考虑末端速度要求后制导环节产生的附加攻角和侧滑角指令。需要制导指令和附加指令相加得到同时考虑落速和落角情况下的合成攻角、侧滑角指令。仿真表明,滑模导引律能稳定姿态且引导飞行器准确到达目标点。针对不同的运动速度情况,进行了落点偏差、末端速度和末端角度随速度的变化趋势分析,在末端角度控制上两种导引律表现相近,在末端速度和落点偏差上滑模导引律表现明显优于最优导引律,表明滑模变结构导引律针对移动目标具有鲁棒性。The sliding mode guidance law of the reentry phase of vehicle was studied considering terminal velocity and impact angle constraints.The sliding mode guidance law satisfying terminal angle was derived, the guidance equations were expressed in longitudinal and lateral plane respectively,and the needed guidance command of angle of attack and sideslip angle were generated.Guidance command of angle of attack and sideslip angle were obtained considering the terminal velocity and falling angle.The synthesized guidance command was the sum of needed guidance command and appended guidance command.Simulation results indicate that the attitude of vehicle is stable and the vehicle is guided to target precisely.The changes of impact point deviation,terminal velocity and impact angle with target velocity were analyzed.The result shows that：the sliding mode guidance law and the optimal guidance law have similar performance on impact angle control,but the former performs much better on terminal velocity and impact point deviation. Therefore,the sliding mode guidance law is robust to maneuvering target.

关 键 词：再入飞行器 末端速度约束 攻击角度约束 滑模变结构导引律 落点偏差 

分 类 号：V412.1[航空宇航科学与技术—航空宇航推进理论与工程]