宇航学报

宇航学报 ›› 2019, Vol. 40 ›› Issue (5): 518-526.doi: 10.3873/j.issn.1000-1328.2019.05.004

• 飞行器设计与力学 • 上一篇    下一篇

深空机动对运载火箭发射火星探测轨道研究

耿光有，王珏，张志国，王建明，田继超   

  1. 1. 北京航空航天大学宇航学院，北京 100191；2. 北京宇航系统工程研究所，北京 100076；
    3. 中国运载火箭技术研究院，北京 100076
  • 收稿日期:2018-09-21 修回日期:2019-02-28 出版日期:2019-05-15 发布日期:2019-05-25
  • 基金资助:

    国家部委预研课题(1591)

Research on Deep Space Maneuver for Earth to Mars Trajectory Design of Long March Launch Vehicle

GENG Guang you, WANG Jue, ZHANG Zhi guo, WANG Jian ming, TIAN Ji chao   

  1. 1.School of Astronautics, Beihang University, Beijing 100191, China; 2. Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China; 3. China Academy of Launch Vehicle Technology, Beijing 100076, China
  • Received:2018-09-21 Revised:2019-02-28 Online:2019-05-15 Published:2019-05-25

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摘要：

为解决长征(LM)运载火箭发射火星探测器转移轨道时，因低温入轨级最长允许滑行时间及测控限制，有效发射日期窗口亟需拓展的问题，采用主矢量理论结合序列二次规划算法(SQP)，研究了探测器深空机动(DSM)对优化运载火箭发射火星转移轨道的作用。在发射直接转移火星探测轨道算法基础上，重点研究了包含引力影响球(SOI)内近地及近火飞行段后，采用主矢量获取深空机动最优猜测初值的分析算法，通过直接使用探测器近火点目标轨道参数优化运载火箭发射轨道，研究对比不同优化目标及设计约束下深空机动的分析结果，证实深空机动对降低转移轨道总发射能量需求、拓展发射日期窗口的高效性；该算法已应用于工程设计。

关键词: 运载火箭发射轨道, 火星探测转移轨道, 深空机动(DSM), 主矢量, 序列二次规划算法(SQP)

Abstract:

In order to resolve the problems of extending the effective launch periods, resulting from the Earth-to-Mars trajectory design of a Long March (LM) launch vehicle constrained by the longest coasting phase and tracking & telecommunication, the primer vector theory and sequence quadratic program (SQP) are used to study the influence of the deep space maneuver (DSM) of a Mars probe on the optimization of the launch vehicle’s Earth-to-Mars trajectory. A brief analysis on the direct Earth-to-Mars trajectory design is given firstly, then details of the algorithm on how to get the optimal initial guess values on DSM through the primer vector theory are studied, including the flight phases inside each gravitational sphere of influence (SOI). Furthermore, with SQP, the launch trajectories via DSM are optimized using the final orbital parameters of the Mars probe directly. The research based on different optimal aims including the design constraints shows that DSM is highly effective to lower the overall launch energy of the Earth-to-Mars transfer trajectory, and to extend the launch periods under the restriction of the longest coasting phase during the parking orbit of the LM launch vehicle. The algorithm has been used in engineering.

Key words:  Launch trajectory, Earth to Mars trajectory, Deep space maneuver (DSM), Primer vector, Sequence quadratic program (SQP)

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