| 整星零动量小卫星偏置飞行姿态解耦控制 |
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| 引用本文： | 罗文成,刘良栋,李果.整星零动量小卫星偏置飞行姿态解耦控制[J].航天控制,1999(1). |
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| 作者姓名： | 罗文成 刘良栋 李果 |
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| 作者单位： | 北京控制工程研究所 |
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| 摘 要： | 研究了采用反作用飞轮为执行机构的整星零动量卫星绕Ｘ轴大角度偏置飞行模式的姿态解耦控制问题。首先给出卫星姿态运动学和动力学模型，然后在控制作用中引入非线性项对姿态动力学模型线性化，进一步对线性模型进行状态反馈解耦和极点配置。最后，给出了数学仿真算例和仿真结果。
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| 关 键 词： | 小型卫星 姿态控制 去耦 |
Attitude Decoupling Control for Biased Flight Mode of Small Satellite in Zero-Momentum State |
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| Luo Wencheng\ Liu Liangdong\ Li Guo Beijing Institute of Control Engineering,Beijing.Attitude Decoupling Control for Biased Flight Mode of Small Satellite in Zero-Momentum State[J].Aerospace Control,1999(1). |
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| Authors: | Luo Wencheng\ Liu Liangdong\ Li Guo Beijing Institute of Control Engineering Beijing |
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| Institution: | Luo Wencheng\ Liu Liangdong\ Li Guo Beijing Institute of Control Engineering,Beijing 100080 |
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| Abstract: | This paper designs an attitude decoupling control law for small satellite in large-angle biased flight mode about roll axis of zero-momentum system via reaction wheels.Attitude kinematics equations and dynamics equations are established firstly in this paper,then a nonlinear item is introduced in the controller to linearize the attitude dynamics equations, and then a state feedback decoupling law and a pole assignment law are designed for the linearized model.At last,a numerical simulation example is given. |
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| Keywords: | Small Satellite Attitude Control Decoupling |
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