| 基于解耦和动态补偿的卫星控制系统设计 |
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| 引用本文： | 何嘉亮,秦世引,万九卿,张伟.基于解耦和动态补偿的卫星控制系统设计[J].航天控制,2005,23(3):30-34. |
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| 作者姓名： | 何嘉亮 秦世引 万九卿 张伟 |
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| 作者单位： | 1. 北京航空航天大学自动化科学与电气工程学院,北京,100083
2. 上海航天控制工程研究所,上海,200233 |
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| 摘 要： | 针对带大型挠性单翼太阳帆板和偏置动量的三轴稳定卫星,研究如何消除星内外干扰对姿态控制精度影响的卫星控制系统的设计问题。首先对星内外干扰进行了数值分析,进而阐明了在经典控制方案中干扰力矩对姿态控制精度的影响,指出经典控制在克服干扰力矩对姿态控制精度影响方面存在的不足之处。然后根据卫星的动力学特点,提出并论证了在设定角动量交换系统标称值条件下基于解耦和动态补偿的卫星控制系统的设计方案。最后深入分析了在该方案下太阳帆板挠性模态的稳定性。
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| 关 键 词： | 单翼太阳帆板 干扰力矩 标称值 解耦 补偿控制 挠性模态 |
| 文章编号： | 1006-3242(2005)00-0030-05 |
| 修稿时间： | 2004年10月15 |
Design of Satellite Control System Based on Decouple Principle and Dynamical Complementary Strategy |
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| He Jialiang,Qin Shiyin,Wan Jiuqing,Zhang Wei.Design of Satellite Control System Based on Decouple Principle and Dynamical Complementary Strategy[J].Aerospace Control,2005,23(3):30-34. |
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| Authors: | He Jialiang Qin Shiyin Wan Jiuqing Zhang Wei |
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| Institution: | He Jialiang~1 Qin Shiyin~1 Wan Jiuqing~1 Zhang Wei~2 1. Beijing University of Aeronautice and Astronautics,Beijing 100083 2. Shanghai Aerospace Institute of Control Engineering,Shanghai 200233 |
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| Abstract: | Design of the control system for 3-axes steady satellite with a large flexible single-wing solar sail and biased momentum is studied so as to remove the effects of disturbance moments from both exterior and interior. Firstly, disturbance moments impacting on satellite are analyzed, then the effect on the attitude control precision is discussed under classical control strategy, thus some disadvantages of the classical control strategy in the aspect of overcoming disturbance effects are pointed out. Afterwards, the design of satellite control system is given based on decouple principle and dynamical complementary strategy under normalized value of momentum exchange system. Finally, the stability of solar sail flexible modes is analyzed in depth. |
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| Keywords: | Single-wing solar sail Disturbance moment Normalized value Decouple principle Compensatory control Flexible modes |
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