一种基于解析规划的多约束再入制导算法  

Reentry Guidance Research with Multi-constrain Based on Analytic Planning Method

作　　者：李强[1] 夏群利[1] 郭涛[2] 温求遒[1] 

机构地区：[1]北京理工大学宇航学院,北京100081 [2]北京航天自动控制研究所,北京100854

出　　处：《弹箭与制导学报》2013年第1期1-4,9,共5页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：博士后科学基金(2011M500008)资助

摘　　要：提出了一种基于H-V剖面的亚轨道飞行器再入制导方法。将再入轨迹分为初始下降段和过渡段分别进行规划,初始下降段采用常值倾侧角飞行,过渡段则采用四次解析多项式进行描述,满足再入走廊约束和能量管理(TAEM)初始条件的同时提高再入轨迹在线规划速度;通过反馈线性化方法设计自适应控制律跟踪标准剖面,同时根据航向误差走廊确定滚转方向,从而完成纵向和侧向的联合设计。仿真结果表明,该制导方法对初始状态偏差和参数不确定性具有较强的鲁棒性。A new reentry guidance algorithm based on H-V profile for reusable launch vehicles was presented. The reentry trajectory was divided into two phases to plan independently, initial descent phase and transition phase. In initial descent phase, a constant bank angle is used to control flight. In transition phase, a fourth order analytic polynomial is used to describe the H-V profile, which can both satisfy the constraints of reentry corridor and terminal area energy management interface, and improve the planning-efficiency. The technique of feed- back linearization is used to obtain an adaptive control law to track longitudinal profile; meanwhile heading error corridor is used to deter- mine lateral motion, which can complete the longitudinal and lateral integrative-design. Simulation results show that the guidance algorithm has strong robustness against initial state errors and uncertain conditions.

关 键 词：亚轨道飞行器 再入走廊 再入制导 H-V剖面 解析规划 反馈线性化 

分 类 号：V448.235[航空宇航科学与技术—飞行器设计]