摘要
进行了基于二体模型和平面三体模型的登月飞行器轨道控制方法的初步研究。首先研究了在二体模型下 ,基于逃逸条件和“远地点可达”条件不同推力作用下的飞行器运动仿真。接着将“远地点可达”概念应用于平面三体模型下的向月飞行的轨道研究 ;完成了从近地低轨道到月球影响球附近的轨道飞行控制方法的研究。仿真结果证明了使用“远地点可达”概念完成地球逃逸段发动机推力终点选择的可行性。
Preliminary research on lunar probe orbit control technology based on planar two bodies model and planar polar three bodies model is introduced in this paper. Under two bodies model, probe trajectory simulation with different thrust modes based on escaping condition and “coverage apogee” condition is studied. Then, “coverage apogee” condition is applied to trajectory study under planar polar three bodies model. Flight trajectories control technology from low earth orbit to lunar sphere of influence (LSOI) is present as well. The result of simulation proves that the concept of “coverage apogee” is feasible to be applied to terminal point selection for earth escaping stage.
出处
《飞行力学》
CSCD
北大核心
2000年第2期46-49,54,共5页
Flight Dynamics
基金
国家 8 63计划航天领域资助!项目 ( 863 -2 -5-3 -1 1 6)
