Attitude control in multi-satellite cooperative observations for distributed remote sensing

Yuan-kun FANG; Bin-wen YUAN; Zi-yang MENG; Gao-fei ZHANG

doi:10.3788/OPE.20192701.0058

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Attitude control in multi-satellite cooperative observations for distributed remote sensing

Micro/Nano Technology and Fine Mechanics | 更新时间：2020-08-13

- Attitude control in multi-satellite cooperative observations for distributed remote sensing
- Optics and Precision Engineering Vol. 27, Issue 1, Pages: 58-68(2019)
- 作者机构：
  
  1.清华大学精密仪器系，北京100084
  2.西昌卫星发射中心，四川西昌 615621
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20192701.0058
  CLC： V474.26
- Received：12 July 2018，
  
  Accepted：16 August 2018，
  
  Published：15 January 2019
- 稿件说明：
移动端阅览
Yuan-kun FANG, Bin-wen YUAN, Zi-yang MENG, et al. Attitude control in multi-satellite cooperative observations for distributed remote sensing[J]. Optics and precision engineering, 2019, 27(1): 58-68.
DOI：

Yuan-kun FANG, Bin-wen YUAN, Zi-yang MENG, et al. Attitude control in multi-satellite cooperative observations for distributed remote sensing[J]. Optics and precision engineering, 2019, 27(1): 58-68. DOI： 10.3788/OPE.20192701.0058.

摘要

针对分布式遥感编队中的协同观测问题，本文开展了多星协同姿态控制研究。首先建立了参考航天器由对日定向到对目标凝视观测的期望姿态，设计了基于姿态、角速度偏差的比例-微分(PD)控制器，证明了闭环系统的李雅普诺夫稳定性。在此基础上，进一步建立了伴飞航天器的期望姿态，为使观测目标在参考航天器、伴飞航天器像平面上的成像位置匹配，以伴飞航天器、参考航天器的姿态之差为基础设计了伴飞航天器的PD控制器，证明了系统的稳定性。最后，对理论结果进行了仿真验证，结果显示伴飞航天器、参考航天器的相对姿态控制误差小于0.01°，精度满足分布式遥感多星协同观测的任务需求。

Abstract

This paper focuses on the cooperative observation problem in multiple spacecrafts. We first establish the desired attitude from the sun orientation to the target starting from the reference spacecraft. A proportional-differential (PD) controller is designed based on attitude and angular velocity deviations. Further

the Lyapunov theorem of the closed-loop system is introduced to prove the stability. Next

we establish the desired attitude for the follower spacecraft. To match the target positions in the image plane for the reference and follower spacecraft

a PD controller is proposed based on the difference of attitude between the reference and follower spacecraft. In addition

the Lyapunov stability of the closed-loop system is demonstrated. Finally

the simulation results show that the attitude control error between the reference and follower spacecraft is less than 0.01°

and the control accuracy satisfies the requirements of distributed remote sensing tasks.

关键词

Keywords

references

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