基于Riccati方程解的再入飞行器制导律设计  

Design of Guidance Law for Reentry Vehicles Based on the Solution of Riccati Equation

作　　者：杨俊春[1] 倪茂林[1] 

机构地区：[1]北京控制工程研究所空间智能控制技术国家级重点实验室,北京100080

出　　处：《航天控制》2006年第4期31-34,共4页Aerospace Control

基　　金：国家自然科学基金重点项目(90405017);973计划项目(2002CB312201-03)资助

摘　　要：提出一种再入飞行器纵向制导律设计方法。首先对纵向运动方程沿着实际轨道线性化,然后利用线性最优调节器原理设计制导律。在每个制导周期内求解代数R iccati方程,利用其正定解构造反馈控制律,与标准轨道的控制量叠加后形成全量控制,用于实际再入轨道的制导。仿真结果表明,所设计的制导律对再入初始偏差具有较强的鲁棒性,同时它也能较好地补偿由于气动参数和大气密度摄动造成的航程误差,从而保证落点精度。A designing per. First, the longitudi method for the longitudinal guidance law of reentry vehicles is presented in this panal dynamic equations are linearized about the actual trajectory. Then the guidance law is designed by using the linear optimal regulator theory. In each guidance period, the algebraic Riccati equation is solved and its solution is used to construct the feedback control law. The feedback control plus the nominal one is used to guide the actual reentry trajectory. Simulation results show the proposed guidance law is robust to deviations from reentry initial states and it can compensate the range error resulting from the per- turbations of aerodynamic parameters and atmospheric density. So the landing point precision is guaranteed.

关 键 词：再入飞行器 纵向制导 RICCATI方程 

分 类 号：TP271.61[自动化与计算机技术—检测技术与自动化装置]