登月飞行器软着陆发动机持续工作初始点选择研究  

ON INITIAL POINT SELECTION OF THE CONTINUED-PROPULSION SOFT-LANDING TRAJECTORIES OF LUNAR PROBES

作　　者：王劼[1] 李俊峰[1] 崔乃刚[2] 刘暾[2] 

机构地区：[1]清华大学工程力学系,北京100084 [2]哈尔滨工业大学航天工程与力学系,哈尔滨150001

出　　处：《工程力学》2003年第6期145-148,共4页Engineering Mechanics

基　　金：中国博士后科学基金(2002117);863计划资助(863-2-5-3-116)

摘　　要：完成了推力幅值恒定的登月飞行器时间最优和燃料最优的软着陆轨道研究。文中将飞行器在月球表面软着陆的轨道分为开普勒下降轨道和制动发动机持续工作轨道两个阶段进行了综合研究。并着重研究了当飞行器从高度为100km的轨道下降到15km近月点时,在近月点附近是否存在一点,在该点软着陆发动机开始持续工作能够更加节省燃料。Time-optimal and fuel-optimal soft-landing trajectories of lunar probes with constant-amplitude thrust are investigated. System model of soft-landing trajectories is established, and parameterization technique and Sequential Quadratic Programming (SQP) method are applied to the normalized model to obtain time-minimum and fuel-minimum trajectories. An integrated study is carried out between two stages of lunar soft-landing trajectories - Keplerian trajectory and continued-propulsion descent trajectory. When lunar probes descend from 100km height to 15km height, the Keplerian trajectory has around 15km high pericynthion. Simulation result shows that there is a point near the pericynthion, and if the continued-propulsion descent trajectory begins at this point other than the pericynthion more fuel will be saved.

关 键 词：飞行器设计 轨道控制 非线性规划 二体问题 登月轨道 软着陆 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]