月球软着陆制导律设计及其误差分析  

Guidance Law Designing and Its Errors Analyzing for Lunar Soft Landing

作　　者：刘浩敏[1] 冯军华[1] 崔祜涛[1] 张泽旭[1] 

机构地区：[1]中国空空导弹研究院,洛阳471009

出　　处：《系统仿真学报》2009年第4期936-938,943,共4页Journal of System Simulation

基　　金：民用航天预研课题

摘　　要：随着任务需求的复杂化,实现高精度定点软着陆是未来月球探测的必然要求。首先,基于简化的软着陆动力学模型,通过求解特殊两点边值问题,给出了一种实时显式制导方法。其次,建立了月球软着陆主制动段的误差模型,并运用误差敏感系数矩阵对所提出制导律的制导误差进行分析。结果表明,与初始位置偏差相比,初始速度偏差对终端各状态的影响要大;位置、速度测量误差分别只对本轴终端位置、速度影响较大;制导律对刻度因素误差最敏感。With the lunar exploring task becoming more and more complex, it is inevitable to realize fixed position soft landing with high precision. Firstly, based on simplified dynamics of lunar soft landing, an explicit guidance law was induced by solving the special two-point boundary value problem. Secondly, error modules of main braking were established and errors of the guidance law designed above were analyzed by error sensitivity coefficient matrixes. The result suggests that compared with initial position deviations, initial velocity deviations have greater influence on the terminal states; initial deviations have large influence on comparative states; additionally, bias scale factor errors have the greatest influence on the guidance law.

关 键 词：月球软着陆 两点边值问题 显式制导 敏感系数矩阵 

分 类 号：V448.233[航空宇航科学与技术—飞行器设计]