摘要
采用地-月低能耗转移轨道的探测器从地球停泊轨道转移到极月轨道一般需要3～4个月时间，这类转移轨道对入轨精度有较高的要求。本文对地月转移轨道中途修正问题进行了研究。文中结合地-月低能耗转移轨道的特点，给出一种分段式多目标多次中途修正方案。利用显式制导结合牛顿迭代，分别以地球和月球作为中心天体求解兰伯特问题，在假设探测器各种轨道误差的基础上进行了蒙特卡罗仿真。采用该方法一般需要3～5次中途修正能够满足月球探测器环月轨道入轨精度要求，整个转移过程燃料消耗小于传统地月转移轨道。文中给出的仿真结果验证了该方案的可行性。
It might take 3 - 4 months to transfer an explorer from a low Earth orbit （LEO） to a low Moon orbit （LMO） using low energy transfer orbit, and the transfer is sensible of the orbit determination accuracy. This paper deals with the midcourse correction of low energy consumption Earth-Moon transfer orbit （LETO）. A new piecewise midcourse correction strategy is presented based on the characteristics of LETO. The explicit guidance combined with Newton iterative method is used to solve the Lambert problem in which Earth and Moon are respectively regarded as the central body. Monte Carlo simulation is achieved based on the supposed error. According to the method, only 3 - 5 times of midcourse corrections are required to satisfy the lunar satellite inject accuracy of polar orbit, and the total fuel consumption of the LETO is less than the one of traditional transfer orbit. Simulation results show the feasibility of the proposed method.
出处
《航天控制》
CSCD
北大核心
2007年第5期22-27,共6页
Aerospace Control
基金
国家自然科学基金资助(批准号:60535010)
关键词
转移轨道
蒙特卡罗仿真
中途修正
Transfer orbit
Monte Carlo simulation
Midcourse correction
