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长征运载火箭发射地火直接转移轨道研究

耿光有 王珏 侯锡云 余梦伦 王建明 张志国

耿光有, 王珏, 侯锡云, 等 . 长征运载火箭发射地火直接转移轨道研究[J]. 北京航空航天大学学报, 2020, 46(1): 20-28. doi: 10.13700/j.bh.1001-5965.2019.0186
引用本文: 耿光有, 王珏, 侯锡云, 等 . 长征运载火箭发射地火直接转移轨道研究[J]. 北京航空航天大学学报, 2020, 46(1): 20-28. doi: 10.13700/j.bh.1001-5965.2019.0186
GENG Guangyou, WANG Jue, HOU Xiyun, et al. Study on Earth-to-Mars direct transfer trajectory by the Long March launch vehicle[J]. Journal of Beijing University of Aeronautics and Astronautics, 2020, 46(1): 20-28. doi: 10.13700/j.bh.1001-5965.2019.0186(in Chinese)
Citation: GENG Guangyou, WANG Jue, HOU Xiyun, et al. Study on Earth-to-Mars direct transfer trajectory by the Long March launch vehicle[J]. Journal of Beijing University of Aeronautics and Astronautics, 2020, 46(1): 20-28. doi: 10.13700/j.bh.1001-5965.2019.0186(in Chinese)

长征运载火箭发射地火直接转移轨道研究

doi: 10.13700/j.bh.1001-5965.2019.0186
详细信息
    作者简介:

    耿光有  男, 博士, 研究员。主要研究方向:长征运载火箭飞行力学与制导总体设计、深空探测轨道动力学等

    王珏  男, 博士, 教授, 博士生导师。主要研究方向:飞行器设计、长征运载火箭总体设计

    通讯作者:

    耿光有, E-mail:genggy@buaa.edu.cn

  • 中图分类号: V412

Study on Earth-to-Mars direct transfer trajectory by the Long March launch vehicle

More Information
  • 摘要:

    针对发射场射向范围和低温入轨级在停泊轨道上最长允许滑行时间严格受限下,工程设计火星探测任务发射轨道时,优化保障2~3周发射日期窗口的困难,以及精确设计拼接探测器分离点时刻轨道6根数耗时周期长等问题,提出了加入滑行时间限制再精确双向微分修正的设计算法(有别于传统B平面矢量法)。由地球影响球边界速度直接解出长征运载火箭入轨点轨道根数,将火箭飞行星下点弧段表示成滑行时间的分析式,快速找到满足诸多设计约束的初始发射轨道;并解决了考虑探测器小幅深空机动后火箭发射轨道的深入优化问题。精确力学模型下数值微分改进后,获得高精度计算结果,同等可比条件下运算精度不低于STK软件。实现了从地面起飞到抵达近火点的飞行轨道整体优化,确保了首次探火工程的顺利实施。

     

  • 图 1  从地球转移至火星的飞行轨道示意图

    Figure 1.  Schematic diagram of Earth-to-Mars flight trajectory

    图 2  探测火星地球出发轨道的几何图示

    Figure 2.  Earth-to-Mars launch trajectory geometry illustration

    图 3  射向AL、飞行航程角θδo关系

    Figure 3.  Contour map of δo with respect to launch azimuth AL and flight range angle θ

    图 4  长征运载火箭设计探测火星轨道示意图

    Figure 4.  Schematic diagram of Long March launch vehicle for Earth-to-Mars trajectory design

    表  1  发射轨道Th=1 849 s, 探测器05 : 25释放, 地球升交出发

    Table  1.   Trajectory Th=1 849 s, probe released on 05 : 25, ascending from the Earth

    轨道根数 EJ2000 SJ2000 ME
    a -21 424.437 km 1.321 527 5 AU -3 816.831 km
    e 1.307 039 0 0.241 839 5 2.020 742 1
    i/(°) 25.405 23.424 93.000
    Ω/(°) 316.214 356.094 156.275
    ω/(°) 293.745 293.291 118.136
    M/(°) 2.781 57.042 0
    Hp 200.0 km 1.001 930 0 AU 500.0 km
    ΔV/(m·s-1) 4 039.207 0 2 446.974
    注:Hp为轨道的近拱点高度(分别相对近地、椭圆近日、近火), M为平近点角。
    下载: 导出CSV

    表  2  发射轨道Th=2 312 s, 探测器03 : 15释放, 地球降交出发

    Table  2.   Trajectory Th=2 312 s, probe released on 03 : 15, descending from the Earth

    轨道根数 EJ2000 SJ2000 ME
    a -21 373.589 km 1.321 389 5 AU -3 815.267 km
    e 1.307 769 4 0.241 822 3 2.021 160 4
    i/(°) 25.372 23.420 93.000
    Ω/(°) 281.242 356.067 156.217
    ω/(°) 325.518 293.283 118.191
    M/(°) 2.790 57.077 0
    Hp 200.0 km 1.001 848 1 AU 500.0 km
    ΔV/(m·s-1) 4 041.078 0 2 447.373
    下载: 导出CSV
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出版历程
  • 收稿日期:  2019-04-24
  • 录用日期:  2019-07-19
  • 刊出日期:  2020-01-20

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