摘要
环月探测器存在需要返回地面的情况,由于环月探测器返回轨道动力学模型的高度非线性,很难从机理上对其进行分析。针对此问题,文章首先建立一种月地转移轨道设计模型,提出了月地转移出发圆的概念,分析并确定了出发圆参数的主要影响因素是返回时间和返回轨道倾角,而后分析了出发圆参数随主要影响因素的变化规律。当返回时间参数N给定时,出发圆具有一定稳定性,基于此分析了恶劣情况下的环月返回机动策略。最后定义Nr作为月球探测器的返回能力量化指标,并给出了不同Nr值对应的速度增量需求。
A lunar orbiter may be required to return to the earth.Because of high nonlinearity of the orbit dynamics model,it is difficult to analyze the return mechanism.In order to solve the problem,a lunar-earth transfer orbit design model is built and a concept of lunar-earth departure circle（LEDC）is developed.The main influence factors on the parameters of LEDC are confirmed to be transfer time Nand return inclination,and then the varying law of the parameter caused by the influence factors is analyzed.As the return time parameter Nis given,the LEDC is stable.And the return policy is studied based on the conclusion.Finally,Nris defined as the parameter to describe the system’s capability of returning to earth and the velocity increments needed for various Nrare given.
出处
《航天器工程》
北大核心
2015年第4期20-26,共7页
Spacecraft Engineering
关键词
环月轨道
返回轨道
月地转移出发圆
lunar orbit
return orbit
lunar-earth departure circle
