| 挠性飞行器飞轮姿态控制系统设计 |
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| 引用本文： | 耿云海,崔祜涛,崔海英,杨涤.挠性飞行器飞轮姿态控制系统设计[J].系统工程与电子技术,2001,23(6):55-58. |
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| 作者姓名： | 耿云海 崔祜涛 崔海英 杨涤 |
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| 作者单位： | 哈尔滨工业大学航天学院, |
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| 摘 要： | 针对带有大型太阳帆板的挠性空间飞行器动力学特性十分复杂的特点，通过合理的假设，采用单轴解耦分析姿态控制系统稳定性问题。采用极点配置法，按照刚体卫星设计系统PID参数，利用根轨迹，确定按刚体卫星参数设计的系统能使挠性空间飞行器控制系统具有渐近稳定性的充分条件；推导系统参数间的关系式，分析挠性空间飞行器主轴姿态控制系统稳定性问题。最后，通过仿真验证了系统的性能。
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| 关 键 词： | 挠性结构 飞行器 姿态控制 |
| 文章编号： | 1001-506X(2001)06-0055-04 |
| 修稿时间： | 2000年5月12日 |
Flexible Spacecraft Attitude Control System Design Using Wheels |
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| Geng Yunhai,Cui Hutao,Cui Haiying,Yang Di.Flexible Spacecraft Attitude Control System Design Using Wheels[J].System Engineering and Electronics,2001,23(6):55-58. |
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| Authors: | Geng Yunhai Cui Hutao Cui Haiying Yang Di |
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| Institution: | Geng Yunhai\ \ Cui Hutao\ \ Cui Haiying\ \ Yang Di School of Astronautics,Harbin Institute of Technology,150001 |
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| Abstract: | Because the dynamics' property of the flexible spacecraft with large solar panels is very complex, decoupling method is adopted to study the stability of the attitude control system for single axis through suitable assumption. The system PID parameters are designed using polar assignment according to rigid satellite. Then with root locus method, the sufficient condition is determined that the system designed by rigid satellite parameter ensures the stability of flexible spacecraft control system. The relation among parameters is derived and the stability of single axis flexible spacecraft attitude control system is studied. At last, the system performance is verified by simulation. |
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| Keywords: | Flexible structure Vechicle Attitude control |
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