航天器受迫绕飞构型设计与控制

张冉; 殷建丰; 韩潮

doi:10.13700/j.bh.1001-5965.2016.0768

航天器受迫绕飞构型设计与控制

doi: 10.13700/j.bh.1001-5965.2016.0768

张冉¹,
殷建丰²,
韩潮^1, ,

1.
北京航空航天大学宇航学院, 北京 100083
2.
北京空间飞行器总体设计部, 北京 100194

详细信息

作者简介:
张冉男, 博士研究生。主要研究方向:航天器编队飞行动力学与控制

韩潮男, 博士, 教授, 博士生导师。主要研究方向:航天器动力学与控制、航天器导航、制导与控制、航天系统动力学仿真等

通讯作者:
韩潮, E-mail: hanchao@buaa.edu.cn

中图分类号: V412.4
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出版历程
- 收稿日期: 2016-09-29
- 录用日期: 2016-12-16
- 网络出版日期: 2017-10-20

Spacecraft forced fly-around formation design and control

1.
School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2.
Beijing Institute of Spacecraft System Engineering, Beijing 100194, China

More Information

Corresponding author: HAN Chao, E-mail:hanchao@buaa.edu.cn

摘要

摘要:
针对航天器在轨服务任务对绕飞技术的要求，研究了航天器受迫绕飞构型设计和控制问题。基于C-W（Clohessy-Wiltshire）方程的解析解，提出了双水滴拼接绕飞构型，并将单脉冲或双脉冲受迫绕飞延展至多脉冲绕飞构型设计；推导了伴随航天器初始状态变量与绕飞构型形状参数的关系，得到了4种构型的解析表达式和脉冲控制策略。通过数值仿真算例验证了设计的4种绕飞构型能够实现伴随航天器的慢速绕飞和快速绕飞，比较了不同绕飞构型的燃料消耗和绕飞距离误差。数值结果表明，双水滴拼接绕飞构型总脉冲最小。研究成果完善了航天器受迫绕飞构型设计与控制的相关理论，为工程应用提供参考。
- 在轨服务 /
- 受迫绕飞 /
- C-W方程 /
- 脉冲控制 /
- 构型设计
Abstract:
In order to meet the requirements of spacecraft fly-around technology in on-orbit service mission, spacecraft forced fly-around formation design and control scheme was investigated. Based on the analytic solution of the C-W(Clohessy-Wiltshire) equations, bi-teardrop formation was proposed. Then multi-impulse fly-around formations were developed after single-or double-impulse formations. The formula between the initial states of following spacecraft and the shape of fly-around formation was derived, and the analytic expressions of four fly-around formations and the impulse control scheme were proposed. Simulation results verify that four designed formations could be used in spacecraft slow fly-around and fast fly-around scenarios. The total fuel consumptions and distance errors of different formations were compared. Numerical results show that bi-teardrop formation has the smallest total impulse. The theory of spacecraft forced fly-around formation design and control is improved, and the results provide reference for engineering application.
- on-orbit service /
- forced fly-around /
- C-W equations /
- impulse control /
- formation design

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图 1 参考航天器LVLH坐标系

Figure 1. Reference spacecraft LVLH coordinate system

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图 2 自然绕飞构型示意图

Figure 2. Schematic diagram of natural fly-around formation

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图 3 双椭圆拼接绕飞构型示意图

Figure 3. Schematic diagram of bi-elliptic joint fly-around formation

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图 4 水滴绕飞构型示意图

Figure 4. Schematic diagram of teardrop fly-around formation

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图 5 不同绕飞周期系数的水滴绕飞形状

Figure 5. Teardrop fly-around shapes with different fly-around period coefficients

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图 6 双水滴拼接绕飞构型示意图

Figure 6. Schematic diagram of bi-teardrop joint fly-around formation

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图 7 多脉冲绕飞构型示意图

Figure 7. Schematic diagram of multi-impulse fly-around formation

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图 8 受迫绕飞总脉冲随脉冲次数曲线

Figure 8. Curves of forced fly-around total impulse with numbers of impulse

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图 9 不同脉冲次数慢速绕飞构型形状示意图

Figure 9. Schematic diagram of slow fly-around formation shape with different numbers of impulse

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图 10 不同脉冲次数快速绕飞构型形状示意图

Figure 10. Schematic diagram of fast fly-around formation shape with different numbers of impulse

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图 11 不同慢速绕飞构型示意图

Figure 11. Schematic diagram of different slow fly-around formations

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图 12 不同快速绕飞构型示意图

Figure 12. Schematic diagram of different fast fly-around formations

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图 13 绕飞单位化脉冲随绕飞周期变化曲线

Figure 13. Curves of fly-around unitized impulse with different fly-around periods

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图 14 绕飞距离误差随绕飞周期变化曲线

Figure 14. Curves of fly-around distance errors with different fly-around periods

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表 1 慢速绕飞总脉冲比较

Table 1. Comparison of slow fly-around total impulse

绕飞构型	次数	方向	总脉冲大小/ (m·s^-1)	单位化脉冲/ (m·s^-1·km^-1)
双椭圆拼接绕飞	2	径向	2.03	0.893
单水滴绕飞	1	径向	1.275	0.891
双水滴拼接绕飞	2	迹向	0.622	0.366
多脉冲绕飞	3	混合	1.299	1.145

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表 2 快速绕飞总脉冲比较

Table 2. Comparison of fast fly-around total impulse

冲绕飞构型	次数	方向	总脉冲大小/ (m·s^-1)	单位化脉冲/ (m·s^-1·km^-1)
双椭圆拼接绕飞	2	径向	2.895	3.019
单水滴绕飞	1	径向	5.79	2.997
双水滴拼接绕飞	2	迹向	2.841	2.00
多脉冲绕飞	3	混合	3.049	3.315

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