轨道拦截问题的一种精确初制导方法研究  

A Precise Initial Guidance Law for Orbit Interception

作　　者：汤一华[1] 陈士橹[1] 徐敏[1] 万自明[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《飞行力学》2006年第4期53-56,共4页Flight Dynamics

摘　　要：对于轨道拦截问题,给出了一种基于速度增益制导和状态转移矩阵的精确初制导方法。该初制导方法能补偿制导方法误差和轨道摄动对拦截脱靶量的影响。仿真结果表明,所提出的精确初制导方法合理、有效,能在增加较小燃料消耗的情况下,大大提高轨道拦截的制导精度。In this paper, the precise initial guidance law based on velocity gain guidance and the state transition matrix for orbit interception were proposed. The miss distance caused by guidance method error and the effects of perturbation are compensated in this initial guidance law. The simulation results show that the precise initial guidance method is rational and efficient, and it can greatly improve the accuracy of orbit interception with an extra little fuel consuming.

关 键 词：轨道拦截 初制导 速度增益 状态转移矩阵 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]