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基于三体系统平动点轨道的环日全景任务轨道设计

蒋卓乐 王亚敏 张永合

蒋卓乐, 王亚敏, 张永合. 基于三体系统平动点轨道的环日全景任务轨道设计[J]. 空间科学学报. doi: 10.11728/cjss2022.05.210830094
引用本文: 蒋卓乐, 王亚敏, 张永合. 基于三体系统平动点轨道的环日全景任务轨道设计[J]. 空间科学学报. doi: 10.11728/cjss2022.05.210830094
JIANG Zhuole, WANG Yamin, ZHANG Yonghe. Trajectory Design of Solar Ring Mission Based on Libration Point Trajectory of Three-body System (in Chinese). Chinese Journal of Space Science, xxxx, x(x): x-xx doi: 10.11728/cjss2022.05.210830094
Citation: JIANG Zhuole, WANG Yamin, ZHANG Yonghe. Trajectory Design of Solar Ring Mission Based on Libration Point Trajectory of Three-body System (in Chinese). Chinese Journal of Space Science, xxxx, x(x): x-xx doi: 10.11728/cjss2022.05.210830094

基于三体系统平动点轨道的环日全景任务轨道设计

doi: 10.11728/cjss2022.05.210830094
详细信息
  • 中图分类号: V412

Trajectory Design of Solar Ring Mission Based on Libration Point Trajectory of Three-body System

  • 摘要: 在空间开展太阳观测是研究太阳活动周、太阳爆发、极端天气等事件起源的重要手段。环日全景探测计划是为实现从黄道面360°全方位观察太阳行星际空间而提出的。本文针对环日全景探测计划,构建了基于三体系统平动点低能量轨道的环日全景轨道部署方法。该方法以日-地L1/L2点Halo轨道幅值、Halo轨道离轨点为变量,以转移轨道飞行时间、入轨机动大小为评价指标,基于三体系统不变流形构建环日全景的转移轨道,并开展轨道优化设计。采用等高线图对设计变量、任务成本进行了全局分析。仿真计算表明,轨道部署无法同时满足飞行时间最短、入轨机动最小要求。设计了轨道机动约束条件下的最优飞行时间解,并给出了基于长三甲运载火箭的一箭双星发射及入轨方案。

     

  • 图  1  从L2点出发的不稳定不变流形

    Figure  1.  Unstable invariant manifolds from L2

    图  2  环日全景四星观测构型

    Figure  2.  Observation configuration of solar Ring mission

    图  3  基于不变流形的环日全景部署轨道优化设计方法

    Figure  3.  Flowchart of the design method for solar ring mission trajectory based on invariant manifolds

    图  4  Halo轨道周期30等分

    Figure  4.  30 equal division of the Halo orbit

    图  5  L1不变流形105度相位

    Figure  5.  Invariant manifolds of L1 for 105-degree deployment

    图  6  L2不变流形105度相位

    Figure  6.  Invariant manifolds of L1 for 105-degree deployment

    图  7  从L1点出发的转移时间等高线

    Figure  7.  Contour map of transfer time for L1 departure

    图  8  从L2点出发的转移时间等高线

    Figure  8.  Contour map of transfer time for L2 departure

    图  9  从L1点出发的速度增量等高线

    Figure  9.  Contour map of phasing maneuver for L1 departure

    图  10  从L2点出发的速度增量等高线

    Figure  10.  Contour map of phasing maneuver for L2 departure

    图  11  轨道机动≤0.75 km·s–1区域的飞行时间等高线图

    Figure  11.  Contour map of flight time corresponding to phasing maneuver less than 0.75 km·s–1

    图  12  日-地旋转坐标系中的最优飞行轨道

    Figure  12.  Optimal transfer trajectories with constrained phasing maneuver in the Sun-Earth rotation system

    表  1  本文方案与论文[9]方案对比

    Table  1.   Contrast between the scheme of this paper and the scheme of Ref. [9]

    论文[9]方案本文方案
    运载火箭 长三甲 长三甲
    发射方式 一箭双星 一箭双星
    发射质量/kg 1375 1450
    运载余量/kg 0 170
    四星质量/kg A/C星500(余量40 kg)
    B/D星875(余量43 kg)
    均为640(含50 kg余量)
    航天器干重/kg 460 460
    部署完成时间/年 6.50 6.38
    下载: 导出CSV
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出版历程
  • 录用日期:  2021-12-24
  • 网络出版日期:  2022-09-17

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