航空、宇航工程:2017,Vol:36,Issue(9):1464-1471
引用本文:
李青, 李静, 冯咬齐, 刘磊. 航天器微振动一体化建模与控制研究[J]. 机械科学与技术
Li Qing, Li Jing, Feng Yaoqi, Liu Lei. Integrated Micro-vibration Modeling and Control Investigation of Spacecrafts[J]. Journal Of Remote Sensing

航天器微振动一体化建模与控制研究
李青1, 李静2, 冯咬齐3, 刘磊1
1. 西北工业大学航天学院, 西安 710072;
2. 大连理工大学航空航天学院, 辽宁大连 116024;
3. 北京卫星环境工程研究所, 北京 100094
摘要:
为实现航天器载荷的高精高稳控制,研究了航天器微振动一体化集成建模与控制方案。首先,根据航天器典型微振动源构建航天器本体微振动的动力学与控制集成模型,并对其进行姿态控制仿真。然后进一步构建包含载荷-本体隔振界面的航天器微振动集成动力学与控制模型,为比较分析被动控制隔振与主被动控制隔振,分别仿真了对载荷被动隔振以及主被动混合隔振两种方案下的姿态控制。结果证实主被动控制混合隔振可有效提高载荷姿态精度和稳定度2个数量级,实现了航天器载荷的高精度高稳定度控制。
关键词:    航天器微振动    集成建模    姿态控制    主被动混合隔振   
Integrated Micro-vibration Modeling and Control Investigation of Spacecrafts
Li Qing1, Li Jing2, Feng Yaoqi3, Liu Lei1
1. School of Astronautics, Northwest Polytechnical University, Xi'an 710072, China;
2. School of Aeronautics and Astronautics, Dalian University of Technology, Liaoning Dalian 116024, China;
3. Beijing Institute of Spacecraft Environment Engineering, Beijing 100094, China
Abstract:
The integrated micro-vibration modeling and control scheme are thus investigated to achieve high accuracy and high stability control of the spacecraft payload. At first, the integrated model including the dynamics and control of the spacecraft body containing typical vibration sources is derived. The attitude control simulation of the spacecraft is implemented. Then, using the proposed model of the spacecraft body, the integrated model of the whole spacecraft containing the payload-body vibration isolator is derived. To compare the performance of the passive vibration isolation and passive-active hybrid isolation, the attitude control of payload is simulated. The simulation results confirm that the passive-active hybrid isolation improves the accuracy and stability of the payload attitude control by two orders. The high accuracy and high stability control of the spacecraft payload is thus achieved.
Key words:    micro-vibration of spacecraft    integrated modeling    attitude control    passive-active hybrid vibration isolation   
收稿日期: 2016-04-07     修回日期:
DOI: 10.13433/j.cnki.1003-8728.2017.0925
基金项目: 国家自然科学基金项目(51675430,11402044)、中央高校基本科研业务费前瞻布局类(3102015BJ(11)MYZ16)及可靠性与环境工程技术重点实验室开放基金项目(KHZS20143003)资助
通讯作者: 刘磊(联系人),副教授,博士,Leiliu@nwpu.edu.cn     Email:Leiliu@nwpu.edu.cn
作者简介: 李青(1993-),硕士研究生,研究方向为光电系统控制、飞行器动力学与控制,qingli029@mail.nwpu.edu.cn
相关功能
PDF(1221KB) Free
打印本文
把本文推荐给朋友
作者相关文章
李青  在本刊中的所有文章
李静  在本刊中的所有文章
冯咬齐  在本刊中的所有文章
刘磊  在本刊中的所有文章

参考文献:
[1] 庞世伟,杨雷,曲广吉.高精度航天器微振动建模与评估技术最近进展[J].强度与环境,2007,34(6):1-9 Pang S W, Yang L, Qu G J. New development of micro-vibration integrated modeling and assessment technology for high performance spacecraft[J]. Structure & Environment Engineering, 2007,34(6):1-9(in Chinese)
[2] 王红娟,王炜,王欣,等.航天器微振动对空间相机像质的影响[J].光子学报,2013,42(10):1212-1217 Wang H J, Wang W, Wang X, et al. Space camera image degradation induced by satellite micro-vibration[J]. Acta Photonica Sinica, 2013,42(10):1212-1217(in Chinese)
[3] 谭天乐,朱春艳,朱东方,等.航天器微振动测试、隔离、抑制技术综述[J].上海航天,2014,31(6):36-45,51 Tan T L, Zhu C Y, Zhu D F, et al. Overview of micro-vibration testing, isolation and suppression technology for spacecraft[J]. Aerospace Shanghai, 2014,31(6):36-45,51(in Chinese)
[4] 刘芳,徐嘉,张燕,等.光学器件微振动引起的光束指向稳定性分析[J].光学学报,2011,31(11):1120001 Liu F, Xu J, Zhang Y, et al. Analysis on beam directing stability problem caused by micro-vibration of optical components[J]. Acta Optica Sinica, 2011,31(11):1120001(in Chinese)
[5] Chapel J, Stancliffe D, Bevacqua T, et al. Guidance, navigation, and control performance for the GOES-R spacecraft[J]. CEAS Space Journal, 2015,7(2):87-104
[6] Markley F L, Bauer F H, Deily J, et al. Attitude control system conceptual design for geostationary operational environmental satellite spacecraft series[J]. Journal of Guidance, Control, and Dynamics, 1995,18(2):247-255
[7] 张猛,祝晓丽,陆娇娣,等.一种高稳定度太阳帆板驱动机构控制方法[J].空间控制技术与应用,2010,36(4):46-49,62 Zhang M, Zhu X L, Lu J D, et al. A high stablity control method for solar array drive mechanism[J]. Aerospace Control and Application, 2010,36(4):46-49,62(in Chinese)
[8] Tursun M, Eşkinat E. Suppression of vibration using passive receptance method with constrained minimization[J]. Shock and Vibration, 2008,15(6):639-654
[9] Bahrami A, Masoule M T, Bahrami M N. Fuzzy control of piezoelectric stewart platform for active vibration control purpose[J]. Transaction on Control and Mechanical Systems, 2012,1(8):356-361
[10] 刘磊.航天器主动隔振及精确定向控制技术研究[D].哈尔滨:哈尔滨工业大学,2011 Liu L. Research on active vibration isolation and precision pointing control for spacecraft[D]. Harbin:Harbin Institute of Technology, 2011(in Chinese)
[11] Pedreiro N, Trankle T L, Tenerelli D J. Control system for terrestrial planet finder interferometer[C]//Proceedings of SPIE 4852, Interferometry in Space, August 22, 2002, Waikoloa, Hawai'i, United States. Waikoloa, Hawai'i, United States:SPIE, 2003:581-592
[12] Winthrop M F, Cobb R G. Survey of state-of-the-art vibration isolation research and technology for space applications[C]//Proceedings of SPIE 5052, Smart Structures and Materials 2003:Damping and Isolation, March 2, 2003, San Diego. San Diego, CA:SPIE, 2003:13-26
[13] 蔡鹏.挠性航天器建模与姿态控制系统研究[D].哈尔滨:哈尔滨工业大学,2008 Cai P. Dynamic modeling and attitude control for flexible spacecraft[D]. Harbin:Harbin Institute of Technology, 2008(in Chinese)
[14] 周伟勇.航天器飞轮动力学建模与振动控制研究[D].长沙:国防科学技术大学研究生院,2012 Zhou W Y. Research on dynamic modeling and vibration control for the flywheel of spacecraft[D]. Changsha:Graduate School of National University of Defense Technology University, 2012(in Chinese)
[15] 周伟敏,张子龙,施桂国,等.帆板驱动微振动对卫星的影响与对策[J].噪声与振动控制,2014,34(2):59-62 Zhou W M, Zhang Z L, Shi G G, et al. Analysis of micro-vibration of a solar array drive mechanism in a satellite and the countermeasure for suppressing the vibration[J]. Noise and Vibration Control, 2014,34(2):59-62(in Chinese)
[16] Hanieh A A. Active isolation and damping of vibrations via Stewart platform[D]. Bruxelles:Universite Libre de Bruxelles, 2003