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基于星下点机动的再入飞行器离轨规划

史树峰 师鹏 赵育善

史树峰, 师鹏, 赵育善等 . 基于星下点机动的再入飞行器离轨规划[J]. 北京航空航天大学学报, 2018, 44(10): 2141-2148. doi: 10.13700/j.bh.1001-5965.2018.0107
引用本文: 史树峰, 师鹏, 赵育善等 . 基于星下点机动的再入飞行器离轨规划[J]. 北京航空航天大学学报, 2018, 44(10): 2141-2148. doi: 10.13700/j.bh.1001-5965.2018.0107
SHI Shufeng, SHI Peng, ZHAO Yushanet al. Deorbit planning of reentry vehicles using ground track manipulation[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(10): 2141-2148. doi: 10.13700/j.bh.1001-5965.2018.0107(in Chinese)
Citation: SHI Shufeng, SHI Peng, ZHAO Yushanet al. Deorbit planning of reentry vehicles using ground track manipulation[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(10): 2141-2148. doi: 10.13700/j.bh.1001-5965.2018.0107(in Chinese)

基于星下点机动的再入飞行器离轨规划

doi: 10.13700/j.bh.1001-5965.2018.0107
基金项目: 

国家自然科学基金 11572019

详细信息
    作者简介:

    史树峰  男, 博士研究生。主要研究方向:航天动力学与控制

    赵育善  男, 博士, 教授, 博士生导师。主要研究方向:航天动力学与控制

    通讯作者:

    赵育善, E-mail:yszhao@buaa.edu.cn

  • 中图分类号: V412.4

Deorbit planning of reentry vehicles using ground track manipulation

Funds: 

National Natural Science Foundation of China 11572019

More Information
  • 摘要:

    针对约束再入点地理位置的再入飞行器离轨问题,提出了一种基于星下点机动的离轨规划方法。再入飞行器的离轨轨道设计受到飞行器当前轨道状态和再入点参数的约束。首先,基于轨道飞行原理,建立了一般椭圆轨道冲量模型下离轨制动参数和再入点参数的关系,分析了最优离轨的推力施加原则;其次,在考虑地球自转的前提下,提出了直接离轨必要条件,针对约束再入点经纬度的问题,完善了利用非线性规划优化方法确定有限推力模型下离轨点位置的策略,同时给出了符合燃料最优目标的离轨制动参数;最后,探讨了一般情况下初始轨道不满足直接离轨必要条件时,为满足星下点约束而进行的轨道机动施加策略。

     

  • 图 1  离轨再入过程示意图

    Figure 1.  Schematic of deorbit and reentry process

    图 2  椭圆轨道制动的制动点与再入点关系

    Figure 2.  Relationship between braking point and reentry point of ellipse orbit braking

    图 3  轨道机动对星下点轨迹的影响

    Figure 3.  Influence of orbit maneuver on ground track

    图 4  离轨制动参数规划流程

    Figure 4.  Flowchart of deorbit braking parametric programming

    图 5  飞行器原轨道的星下点轨迹

    Figure 5.  Ground track of original orbit of vehicle

    图 6  星下点机动结果

    Figure 6.  Results of ground track manipulation

    图 7  离轨过程的星下点轨迹

    Figure 7.  Ground track of deorbit process

    表  1  初始轨道根数

    Table  1.   Initial orbital elements

    参数数值
    a/km6 878.140
    e0.000 3
    i/(°)42.000
    Ω/(°)122.000
    ω/(°)0
    f/(°)220.000
    下载: 导出CSV

    表  2  再入点参数

    Table  2.   Parameters of reentry point

    参数数值
    弹道倾角/(°)-1.800
    地理经度/(°)-75.000
    地理纬度/(°)18.000
    下载: 导出CSV

    表  3  离轨制动参数规划结果

    Table  3.   Planning results of deorbit braking parameters

    参数数值
    离轨时间/s61 676.763
    制动角/(°)-153.635
    推力时间/s164.783
    燃料/kg64.457
    下载: 导出CSV
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出版历程
  • 收稿日期:  2018-03-02
  • 录用日期:  2018-04-09
  • 刊出日期:  2018-10-20

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