单轴储能及姿态控制一体化系统研究

贾宏光; 赵华兵; 白越; 韩邦成; 李正刚; 宣明; 吴一辉

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单轴储能及姿态控制一体化系统研究

微纳科学与技术 | 更新时间：2020-08-12

- 单轴储能及姿态控制一体化系统研究
- Single axis double flywheels integrated power and attitude cortrol system
- 光学精密工程 2004年12卷第5期页码：504-509
- 作者机构：
  
  中国科学院, 长春光学精密机械与物理研究所, 应用光学国家重点实验室, 吉林, 长春, 130033
- 作者简介：
- 基金信息：
  
  国家863计划(No.2002AA715061)();中国科学院预研项目资助(No.42201030108)()
- DOI：
  中图分类号： O231
- 收稿日期：2004-07-22，
  
  修回日期：2004-08-18，
  
  网络出版日期：2004-10-15，
  
  纸质出版日期：2004-10-15
- 稿件说明：
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贾宏光, 赵华兵, 白越, 韩邦成, 李正刚, 宣明, 吴一辉. 单轴储能及姿态控制一体化系统研究[J]. 光学精密工程, 2004,(5): 504-509

JIA Hong-guang, ZHAO Hua-bing, BAI Yue, HAN Bang-cheng, LI Zheng-gang, XUAN Ming, WU Yi-hui . Single axis double flywheels integrated power and attitude cortrol system[J]. Editorial Office of Optics and Precision Engineering, 2004,(5): 504-509
贾宏光, 赵华兵, 白越, 韩邦成, 李正刚, 宣明, 吴一辉. 单轴储能及姿态控制一体化系统研究[J]. 光学精密工程, 2004,(5): 504-509 DOI：

JIA Hong-guang, ZHAO Hua-bing, BAI Yue, HAN Bang-cheng, LI Zheng-gang, XUAN Ming, WU Yi-hui . Single axis double flywheels integrated power and attitude cortrol system[J]. Editorial Office of Optics and Precision Engineering, 2004,(5): 504-509 DOI：

摘要

给出了一种应用于卫星的单轴能量存储及姿态控制一体化系统.在同一轴上安装两个反向旋转的飞轮

通过预定的算法

控制两个飞轮的角加速度

可以在日阳期、日阴期及其过渡过程分别实现能量的储存和释放

并且在这些过程中保持卫星的姿态不变或按要求实现姿态机动.根据实验对系统进行了适当的简化

推导出了其数学模型

给出了相应的控制算法

并进行了在储、放能的同时实现姿态控制过程的试验.初步试验表明

在储能过程中

轴系控制精度优于3°;在放能过程中

轴系控制精度优于1.2′

换算到百公斤量级卫星的姿态角波动量分别为3.6′和1.5″.结果表明:在消除一些不对称因素(如两个电机结构差异)后

此方法在卫星或其它空间飞行器中同时完成能量交换和姿态控制是可行的.

Abstract

A single axis double flywheels integrated power and attitude control system(IPACS)

including its working principle and configuration

are given to simulate the charge

discharge and attitude control process during the full sun

eclipse and their interim. Based on the experiment

the system models during the energy storage and release are obtained and their corresponding control arithmetic is given. Experiments show that the system can be used to store and release energy while adjusting the attitude of the platform

as well as of the satellite. The angle of the platform can be controlled to stabilize within 3° and 1.2′

respectively. To the satellite in which the flywheels can be used

the attitude affection should be less than 3.6′　and 1.5″

respectively. After eliminating unbalance affections

such as the difference from motors

the scheme using flywheels to perform the energy storage and attitude control in the satellite is efficiency.

关键词

Keywords

references

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林来兴. 小卫星通讯技术发展综述及分析[M] . 小卫星技术发展论文集,1995:10-11.LIN L X. A summarize to the communication technology of the satellites [M] .The corpus of satellites technology,1995:10-11.(in Chinese)

CHRISTOPHER D A, BEACH, R. Flywheel technology development program for aerospace applications[J] .IEEE Aerospace and Electronic Systems Magazine, 1998,13(6):9-14.

KENNY B H,KASCAK PE. DC Bus regulation with a flywheel energy storage system[P] . NASA/TM-2002-211897/REV1.

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贾宏光, 张洪华. 集成化储能及姿控系统方案研究报告[R] .中国科学院长春光学精密机械与物理研究,2001.JIA H G,ZHANG H H. Schenme report of the integrated power and attitude control system [R] .Changchun Institute of Opties,Fine Mechanics and Physics,Chinese Academy of Seiences,2001.(in Chinese)

白越, 吴一辉, 宣明. 高速储能飞轮转子设计[J] . 光学精密工程.2003,11(4):13-17.BAI Y,WU Y H,XUAN M.Design of the high speed rotors for the energy storage flywheel[J] . Optics and Precsion engineerinc,2003,11(4):13-17.(in Chinese)

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