航天器微振动一体化建模与控制研究

李青; 李静; 冯咬齐; 刘磊

doi:10.13433/j.cnki.1003-8728.2017.0925

航天器微振动一体化建模与控制研究

doi: 10.13433/j.cnki.1003-8728.2017.0925

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

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

详细信息

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

通讯作者:
刘磊(联系人),副教授,博士,Leiliu@nwpu.edu.cn

计量
- 文章访问数: 248
- HTML全文浏览量: 37
- PDF下载量: 12
- 被引次数: 0
出版历程
- 收稿日期: 2016-04-07
- 刊出日期: 2017-09-05

Integrated Micro-vibration Modeling and Control Investigation of Spacecrafts

Li Qing¹,
Li Jing²,
Feng Yaoqi³,
Liu Lei^{1
, ,}

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

摘要

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。
- 航天器微振动 /
- 集成建模 /
- 姿态控制 /
- 主被动混合隔振
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.
- micro-vibration of spacecraft /
- integrated modeling /
- attitude control /
- passive-active hybrid vibration isolation

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参考文献(16)

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