Staring imaging attitude tracking control of agile small satellite

CHEN Xue-qin; GENG Yun-hai; WANG Feng; LI Dong-bai

doi:10.3788/OPE.20122005.1031

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Staring imaging attitude tracking control of agile small satellite

Article | 更新时间：2020-08-12

- Staring imaging attitude tracking control of agile small satellite
- Optics and Precision Engineering Vol. 20, Issue 5, Pages: 1031-1040(2012)
- 作者机构：
  
  哈尔滨工业大学卫星技术研究所,黑龙江哈尔滨,150080
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20122005.1031
  CLC： V448.22
- Received：02 December 2011，
  
  Revised：29 December 2011，
  
  Published Online：10 May 2012，
  
  Published：10 May 2012
- 稿件说明：
移动端阅览
陈雪芹, 耿云海, 王峰, 李冬柏. 敏捷小卫星对地凝视姿态跟踪控制[J]. 光学精密工程, 2012,20(5): 1031-1040

CHEN Xue-qin, GENG Yun-hai, WANG Feng, LI Dong-bai. Staring imaging attitude tracking control of agile small satellite[J]. Editorial Office of Optics and Precision Engineering, 2012,20(5): 1031-1040
陈雪芹, 耿云海, 王峰, 李冬柏. 敏捷小卫星对地凝视姿态跟踪控制[J]. 光学精密工程, 2012,20(5): 1031-1040 DOI： 10.3788/OPE.20122005.1031.

CHEN Xue-qin, GENG Yun-hai, WANG Feng, LI Dong-bai. Staring imaging attitude tracking control of agile small satellite[J]. Editorial Office of Optics and Precision Engineering, 2012,20(5): 1031-1040 DOI： 10.3788/OPE.20122005.1031.

摘要

研究了基于双框架控制力矩陀螺(DGCMG)的敏捷小卫星对地凝视成像过程中的姿态跟踪控制。首先

根据敏捷小卫星的特点和凝视成像任务需求设计执行机构配置方案。然后

根据轨道信息计算地面凝视目标的相对姿态和角速度;为避免控制力矩陀螺(CMG)奇异性的影响

同时设计了适当的控制律和操纵律。最后

通过在"试验三号卫星"的姿态轨道控制系统仿真平台上增加凝视成像任务需求并调整执行机构配置

建立敏捷小卫星姿态控制系统

对文中设计的方案和控制方法进行了数学仿真验证。仿真结果表明

该算法简单有效

能够实现敏捷小卫星对地凝视姿态跟踪

同时给出了DGCMG能够输出的最小框架角速率指标决定了姿态跟踪精度的结论。

Abstract

The attitude tracking control of staring imaging of an agile small satellite driven by Double-Gimbaled Control Moment Gyroscopes (DGCMG) was investigated. Firstly

an actuator configuration scheme was developed according to the characteristics of agile satellite and the staring imaging mission requirements. Then

the orbit information was used to compute the relative attitude angle and attitude angular velocity of a staring imaging target with respect to the satellite body reference frame

and the proper control law and steering law were introduced to avoid the singularity of Control Moment Gyroscope(CMG). Finally

based on the "SY-3" satellite attitude and orbit control simulation platform

the agile small satellite closed-loop control simulation system was established by taking the mission requirements and the actuator adjustments into account and the proposed design scheme and control method were verified in a mathematical simulation. Obtained results show that the presented solution is effective for staring imaging attitude maneuver control of the agile small satellite and the least gimbal angle rate of DGCMG is the most important factor to determinate attitude tracking precision.

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references

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