编队卫星法向机动的切向耦合效应补偿方法

王有亮; 李明涛; 郑建华; 周敬

doi:10.13700/j.bh.1001-5965.2016.0437

编队卫星法向机动的切向耦合效应补偿方法

doi: 10.13700/j.bh.1001-5965.2016.0437

王有亮^{1, 2, 3},
李明涛^{1, 2, 3, ,},
郑建华^{1, 2, 3},
周敬^{1, 2, 3}

1.
中国科学院国家空间科学中心, 北京 100190
2.
中国科学院复杂航天系统电子信息技术重点实验室, 北京 100190
3.
中国科学院大学, 北京 100049

详细信息

作者简介:
王有亮, 男, 博士研究生。主要研究方向:航天器编队动力学、控制与仿真

李明涛, 男, 博士, 研究员。主要研究方向:航天器动力学、控制与仿真

郑建华, 女, 博士, 研究员, 博士生导师。主要研究方向:飞行器动力学、控制与仿真

通讯作者:
李明涛, E-mail:limingtao@nssc.ac.cn

中图分类号: V412.41
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- 被引次数: 0
出版历程
- 收稿日期: 2016-05-23
- 录用日期: 2016-07-15
- 网络出版日期: 2017-06-20

Compensation method of in-track coupling effect of cross-track maneuver for formation-flying satellites

WANG Youliang^{1, 2, 3},
LI Mingtao^{1, 2, 3
, ,},
ZHENG Jianhua^{1, 2, 3},
ZHOU Jing^{1, 2, 3}

1.
National Space Science Center, Chinese Academy of Sciences, Beijing 100190, China
2.
Key Laboratory of Electronics and Information Technology for Space Systems, Chinese Academy of Sciences, Beijing 100190, China
3.
University of Chinese Academy of Sciences, Beijing 100049, China

More Information

Corresponding author: LI Mingtao, E-mail:limingtao@nssc.ac.cn

摘要

摘要:
空间四面体构型在空间物理场三维立体协同探测任务中具有重要应用价值。为了保证空间四面体良好的探测性能，必须对空间四面体构型进行构型维持控制。但是，在法向控制中，法向机动的切向耦合效应会导致编队构型发生切向漂移，使得空间四面体几何特性变差，从而影响编队卫星的探测性能。针对编队飞行任务，通过解析的补偿方法消除法向机动时由于耦合效应造成的构型切向漂移，从而实现J2摄动下精确的构型初始化重构和构型保持控制。仿真表明，该方法简单有效，能够有效消除J2摄动下的法向机动引起的构型切向漂移，实现更精确的构型控制。
- 编队飞行 /
- 高斯变分方程 /
- 法向机动 /
- 切向漂移 /
- 解析补偿
Abstract:
Tetrahedron formation has an important application in the space physical three-dimensional collaborative detection. Formation keeping control must be carried out to guarantee the detecting efficiency. However, the in-track coupling effect of cross-track maneuver can cause the drift along the in-track direction, thus making the deterioration of geometric characteristic, and having a bad effect on the detecting efficiency. An analytical compensation method for formation-flying satellites was designed to eliminate the in-track drift caused by coupling effect of cross-track maneuver, and achieve the accurate formation initialization reconfiguration and formation keeping control under J2 perturbation. The numerical simulation results show that the method is simple and efficient to eliminate the in-track drift caused by cross-track maneuver under J2 perturbation, and can achieve more accurate formation control.
- formation-flying /
- Gauss variation equation /
- cross-track maneuver /
- in-track drift /
- analytical compensation

HTML全文

图 1 LVLH坐标系示意图

Figure 1. Schematic diagram of LVLH coordinate system

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图 2 法向有限推力作用时卫星轨道半长轴和倾角变化量随时间的变化

Figure 2. Variation of orbital semi-major axis and inclination with time for satellite with cross-track finite thrust

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图 3 法向脉冲推力作用时卫星轨道半长轴和倾角变化量随时间的变化

Figure 3. Variation of orbital semi-major axis and inclination with time for satellite with cross-track impulsive thrust

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图 4 固定方向推力作用时轨道半长轴和倾角变化量随时间的变化

Figure 4. Variation of orbital semi-major axis and inclination with time for satellite with fixed direction thrust

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图 5 卫星编队四面体构型示意图

Figure 5. Schematic diagram of tetrahedron formation of satellites

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图 6 法向距离随时间的变化

Figure 6. Variation of cross-track range with time

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图 7 切向补偿对切向距离变化的影响

Figure 7. Influence of in-track compensation on in-track range

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图 8 切向补偿的速度增量大小和法向机动的速度增量大小的关系

Figure 8. Relationship between velocity increments of in-track compensation over and cross-track maneuver

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