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浙江大学学报(工学版)
J4  2011, Vol. 45 Issue (10): 1771-1776    DOI: 10.3785/j.issn.1008-973X.2011.10.012
自动化技术、信息技术     
皮卫星偏置动量轮在轨备份切换策略
韩柯, 王昊, 朱小丰, 向甜, 金仲和
浙江大学 信息与电子工程系,浙江 杭州 310027
In-orbit backup and switch method for pico-satellite’s
bias momentum wheel
HAN Ke, WANG Hao, ZHU Xiao-feng, XIANG Tian, JIN Zhong-he
Department of Information and Electronics Engineering, Zhejiang University, Hangzhou 310027, China
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摘要：

参考微动量轮的实测数据,讨论并建立描述转速随机变化的马尔可夫模型.在该模型基础上,提出并分析用于皮卫星的偏置动量轮备份、切换策略.该策略定义了4个正常模式和3个异常模式：在普通情况下,系统在正常模式下定时切换飞轮；当故障发生时,系统切入异常模式,隔离故障飞轮.与常规的冷备份方法相比,该策略为飞轮性能、功能的故障检测提供了更方便的途径,同时在更长时间段内,能够保持星体连续姿态稳定.数学仿真表明,应用本文策略,正常情况切换时,造成的姿态扰动最大不超过20°；对于突发故障,切换带来的姿态扰动恢复时间约为30 min.
Abstract:

A Markov model describing rotation speed variation was discussed and established according to a micro momentum wheel test. Then a backup and switch method for pico-satellite’s bias momentum wheel was introduced and analyzed. The method includes four normal modes and three exceptional modes. Generally, system operates in normal modes, periodically switching between two flywheels. When failure arises, system switches to exceptional modes, making the broken wheel isolated. The method provides a more convenient way for both flywheel function and performance failure detection compared with traditional cold backup method; and can keep stabilizing satellite attitude continuously for much longer time. Simulation results show that the application of the method can keep attitude error within 20° in normal switch case; and the attitude disorder due to emergency switch can be restored in about 30 min for accidental flywheel failure.
出版日期: 2011-10-01
:  V 448.22  
基金资助:

中国博士后科学基金资助项目（20080431306）；中国博士后科学基金特别资助项目（20081458）；教育部新世纪优秀人才支持计划资助项目（NCET06051）；高等学校全国优秀博士学位论文作者专项资金资助项目（200035）.
通讯作者: 王昊，男，副教授.     E-mail: roger@zju.edu.cn
作者简介: 韩柯（1984－），男，博士生，从事皮卫星姿态测量及控制系统的设计研究.E-mail: ZJUHank@gmail.com
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引用本文:

韩柯, 王昊, 朱小丰, 向甜, 金仲和. 皮卫星偏置动量轮在轨备份切换策略[J]. J4, 2011, 45(10): 1771-1776.

HAN Ke, WANG Hao, ZHU Xiao-feng, XIANG Tian, JIN Zhong-he. In-orbit backup and switch method for pico-satellite’s
bias momentum wheel. J4, 2011, 45(10): 1771-1776.

链接本文:

https://www.zjujournals.com/eng/CN/10.3785/j.issn.1008-973X.2011.10.012    或    https://www.zjujournals.com/eng/CN/Y2011/V45/I10/1771

［1］ 赵翔宇,金小军,韩柯,等.皮卫星电源系统的设计和仿真［J］.浙江大学学报：工学版, 2009, 43(2): 228-233.
ZHAO Xiangyu, JIN Xiaojun, HAN Ke, et al. Design and simulation of picosatellite power system ［J］. Journal of Zhejiang University: Engineering Science, 2009, 43(2): 228-233.
［2］ 金小军,赵翔宇,辜渝嘉,等.皮卫星在轨能量平衡仿真研究［J］.浙江大学学报：工学版,2009,43(7): 1282-1287.
JIN Xiaojun, ZHAO Xiangyu, GU Yujia, et al. Study on simulation of onorbit energy balance of picosatellite ［J］. Journal of Zhejiang University: Engineering Science, 2009, 43(7): 1282-1287.
［3］ EAGLESON S. Attitude determination and control, detailed design, test, and implementation for CanX2 and preliminary design for CanX3 and CanX45 ［D］. Toronto: University of Toronto, 2006.
［4］ MENG Tao, WANG Hao, JIN Zhonghe, et al. Attitude stabilization of a picosatellite by momentum wheel and magnetic coils ［J］. Journal of Zhejiang University: Science A, 2009, 10(11): 1617-1623.
［5］ 蒙涛,王昊,金仲和,等.基于低成本MEMS传感器的皮卫星融合定姿算法研究［J］.宇航学报,2009,30(4): 1569-1573.
MENG Tao, WANG Hao, JIN Zhonghe, et al. A fusion algorithm for picosatellite attitude determination using low cost MEMSbased sensors ［J］. Journal of Astronautics, 2009, 30(4): 1569-1573.
［6］ 田科丰,李智斌.基于动态逆的卫星姿控系统飞轮故障容错控制［J］.中南大学学报：自然科学版,2009,40(S1): 191-199.
TIAN Kefeng, LI Zhibin. Dynamic inversion based satellite attitude fault tolerant control system with reaction wheel fault ［J］. Journal of Central South University: Science and Technology, 2009, 40(S1): 191-199.
［7］ 梁津津,王青,董朝阳.一种针对卫星执行机构故障的容错控制系统［J］.华中科技大学学报：自然科学版,2009,37(S1): 267-270.
LIANG Jinjin, WANG Qing, DONG Chaoyang. A faulttolerant control system to handle actuator failures of a satellite ［J］, Journal of Huazhong University of Science and Technology: Natural Science Edition, 2009, 37(S1): 267-270.
［8］ ISMAIL Z, VARATHARAJOO R. A study of reaction wheel configurations for a 3axis satellite attitude control ［J］. Advances in Space Research, 2010, 45(6): 750-759.
［9］ ZHOU Jinglun, LIU Qiang, JIN Guang, et al. Reliability modeling for momentum wheel based on data mining of failurephysics ［C］∥ 2010 3rd International Conference on Knowledge Discovery and Data Mining. Phuket, Thailand: IEEE, 2010.
［10］ CHANG YK. LEE BH, KIM SJ. Momentum wheel startup method for HAUSAT2 ultrasmall satellite ［J］. Aerospace Science and Technology, 2006, 10(2): 168-174.
［11］ SILANI E, LOVERA M. Magnetic spacecraft attitude control: a survey and some new results ［J］. Control Engineering Practice, 2005, 13(3): 357-371.
［12］ 屠善澄.卫星姿态动力学与控制(2)［M］. 北京:中国宇航出版社,1998: 282-293.
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