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一种探月任务多窗口发射轨道设计方法
唐明亮1, 王颖1, 张学功1, 古艳峰1, 卢亮亮2
1.上海宇航系统工程研究所, 上海 201109;2.探月与航天工程中心, 北京 100037
摘要:
针对探月任务多窗口发射需求和目标轨道受到明显月球引力摄动的特点,提出一种快速高效的发射轨道设计方法:在星箭分离前的发射段,各发射窗口对应的发射轨道的一、二级飞行段完全相同,仅调整三级工作段程序角和无动力滑行时间,以满足入轨要求;在末级排放段,微调末级速度方向,利用月球摄动抬高末级近地点高度,使之超过GEO受保护区。该方法可统一火箭一、二级飞行段状态,缩小子级残骸落区范围,增强入轨参数设计的灵活性,显著提高星箭入轨参数迭代和相关分析工作的效率,明显改善末级离轨效果,符合空间安全相关要求,可推广应用于其他深空探测任务的多窗口发射轨道设计。
关键词:  嫦娥4号;中继星;长征4号丙;发射轨道
DOI:10.15982/j.issn.2095-7777.2017.02.003
分类号:V412.4+1
基金项目:
A Design Method of Multi-Window Launch Trajectories Design for Lunar Exploration Mission
TANG Mingliang1, WANG Ying1, ZHANG Xuegong1, GU Yanfeng1, LU Liangliang2
1.Aerospace System Engineering Shanghai, Shanghai 201109, China;2.Center of Lunar Exploration and Space Program, Beijing 100037, China
Abstract:
Aiming at multi-window launch requirements as well as the target orbit's property of strong lunar perturbation in lunar exploration mission,a quick and efficient design method of launch trajectory is presented in this paper. During the launch phase before Spacecraft/Launch Vehicle(SC/LV)separation,each launch window has the same trajectory in the first and second stage flight sections,only the program angles of third stage work sections and the durations of coast sections need to be adjusted to satisfy injection requirements. During the orbital stage passivation phase,in order to raise the perigee altitude of orbital stage above GEO protected region,its velocity direction is properly modified with the help of lunar perturbation. This method can consolidate LV's status in first and second stage fight sections,reduce sub-stages' impact zones,strengthen the flexibility of injection parameter design,enhance the effieciency of injection parameter iteration and relative analyses,obviously improve the de-orbit effect of orbital stage,meet the requirements of space safety. This method can be applied to multi-window launch trajectory design for other deep space missions.
Key words:  Chang'e-4;relay satellite;CZ-4C;launch trajectory