月球探测再入返回试验后续飞行方案研究  

Follow-up Flight Scheme for the Reentry Test of China Lunar Exploration

作　　者：刘磊[1,2] 唐歌实[1,2] 胡松杰[1,2] 陈略[1,2] 刘勇[1,2] 谢剑锋[1,2] 周建亮[2] 

机构地区：[1]航天飞行动力学技术重点实验室,北京100094 [2]北京航天飞行控制中心,北京100094

出　　处：《宇航学报》2015年第1期9-17,共9页Journal of Astronautics

基　　金：国家自然科学基金(11303001,11203003,11373013,11173005);探月工程重大科技专项

摘　　要：对于中国月球探测再入返回飞行试验的剩余推进剂,研究并设计了后续飞行方案。首先,基于月球探测再入返回飞行试验任务结束后的轨道和卫星状况,分析了可行的探测目标,确定了以日地月空间和相应平动点作为探测目标的后续飞行方案。其次,针对后续飞行方案中的轨道设计与控制需求,研究了平动点轨道直接转移入轨方法和不同系统的平动点轨道转移方法。相对于目前常见的基于不变流形的平动点转移轨道设计方法,文章方法无需进行大量的流形计算,因而计算步骤简单,计算量大大降低,尤其便于实际飞行任务应用。最后,设计了后续飞行方案的飞行轨道和相应的控制方案,同时分析了控制操作的地面测控条件。研究结果表明,基于月球探测再入返回飞行试验任务的剩余推进剂,完全可以在日地月空间开展多项具有创新性和重要应用价值的飞行试验验证,为我国后续"夸父"和月球探测等深空探测任务积累宝贵的测控技术和经验,同时为后续深空探测的"多目标多任务"设计思路提供有益借鉴。Flight scheme utilizing the remaining propellant of the reentry test of China lunar exploration is investigated in this article. First,according to the trajectory and satellite status at the end of the reentry mission,the feasible flight goals are analyzed. Consequently,the flight scheme is designed with the flight goal of collinear libration points in the sunearth / moon and the earth-moon systems. Second,for the requirements of trajectory design and control in the scheme,the methods of direct orbit transfer and orbit entry to libration point and orbit transfer between different libration points are investigated. Compared with the present method of trajectory design based on the invariant manifold,these methods need no or less calculation of manifolds and have a simpler calculation procedure. Therefore,the methods can greatly decrease the calculation burden,and are suitable to the actual flight mission. Finally,the trajectory and control plan are designed for the flight scheme based on the above methods. Furthermore,the corresponding TT＆C condition is analyzed for all maneuvers.This research shows that some innovative and valuable flight tests can be performed and testified in the sun-earth / moon space by use of the remaining propellant of the reentry test mission,which are significant to accumulate valuable TT＆C technique and experience for the future‘Kuafu’mission,lunar missions,and some other deep space exploration of China.Additionally,this research is especially beneficial and applicable to a future multi-mission instance in the deep space exploration.

关 键 词：再入返回试验 月球探测 飞行方案 轨道设计 平动点 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]