摘要
文中的软着陆过程从一条环月停泊轨道开始。一旦选定着陆点 ,则通过ΔV变轨转入一条椭圆轨道。当到达近月点时 ,着陆制动发动机点火 ,开始动力下降阶段。参考运载火箭制导过程的分析方法 ,假设月球为一均匀引力场 ,以燃耗最优性为出发点 ,提出了一种用于软着陆动力下降过程的显式制导律。其显式表达式是剩余时间的函数。它不必进行迭代计算 。
The lunar soft landing in this paper begins from a circular lunar parking orbit. Once the landing area has been selected, and it is time to de orbit for landing, a Δ V burn is performed to establish an elliptical orbit. At perilune the landing thruster is ignited, and a propulsive landing is performed. Similar to the guidance of launch vehicles, a uniform gravity field on lunar surface is assumed. An explicit guidance law for powered descending phase is proposed to minimize the fuel consumption. The law is a function of the time to go. Iterative calculation is not needed. It is an explicit easily mechanized sub optimal guidance law.
出处
《宇航学报》
EI
CSCD
北大核心
2000年第4期55-63,共9页
Journal of Astronautics
基金
国家自然科学基金资助项目!(19782 0 0 4)
