| 帆板转动时卫星姿态的非线性控制 |
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| 引用本文： | 李英堂,费从宇.帆板转动时卫星姿态的非线性控制[J].宇航学报,2001,22(1):31-36. |
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| 作者姓名： | 李英堂 费从宇 |
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| 作者单位： | 上海卫星工程研究所, |
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| 摘 要： | 当帆板转动时，卫星姿态因系统质量特性的改变和帆板驱动力矩的作用而发生扰动，本文采用一种具有鲁棒性的非线性控制方法，实现了高精度的卫星姿态控制。
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| 关 键 词： | 卫星 姿态控制 太阳帆板 非线性控制 鲁棒性 转动 |
| 文章编号： | 1000-1328（2001）01-0031-06 |
| 修稿时间： | 1999年9月24日 |
A NONLINEAR APPROACH OF
SATELLITE ATTITUDE CONTROL AS ROTATING SOLAR ARRAY WING |
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| Li Yingtang,Fei Congyu.A NONLINEAR APPROACH OF
SATELLITE ATTITUDE CONTROL AS ROTATING SOLAR ARRAY WING[J].Journal of Astronautics,2001,22(1):31-36. |
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| Authors: | Li Yingtang Fei Congyu |
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| Abstract: | As rotating solar array wing about a satellite body,the control performance of satellite attitude will be deteriorated by the uncertainty of satellite inertia and the disturbance of solar array wing drive torque.In order to improve the attitude control accuracy,a robust control law of satellite attitude is developed based on a kind of nonlinear control method.The stability of the control law is assured according to the Lyapunov stability theory.A real simulation example also verifies that the nonlinear control law designed is more effective than traditional linear control law. |
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| Keywords: | Satellite Attitude control Solar array wing Nonlinear control Robust |
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