| 根据线性迭加理论实现微小卫星姿态磁控制 |
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| 引用本文： | 李太玉,张育林.根据线性迭加理论实现微小卫星姿态磁控制[J].上海航天,2006,23(1):1-7. |
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| 作者姓名： | 李太玉 张育林 |
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| 作者单位： | 1. 上海航天技术研究院,上海,200235
2. 酒泉卫星发射中心,甘肃,酒泉,732750 |
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| 摘 要： | 根据地磁力矩定向阻尼特性和线性迭加理论,提出仅用磁力矩器实现对地指向微小卫星三轴姿态稳定的控制律。推导了采用迭加补偿,并考虑附加磁矩影响时改进的卫星姿态动力学方程。理论分析和仿真结果表明,该控制律简单、姿态控制精度高。
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| 关 键 词： | 微小卫星 姿态控制 磁力矩器 附加磁矩 稳定性 |
| 文章编号： | 1006-1630（2006）01-0001-07 |
| 收稿时间： | 2005-06-14 |
| 修稿时间： | 2005-10-13 |
Micro-Satellite Magnetic Attitude Control Basing on Theory of Linearity Superposition |
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| LI Tai-yu,ZHANG Yu-lin.Micro-Satellite Magnetic Attitude Control Basing on Theory of Linearity Superposition[J].Aerospace Shanghai,2006,23(1):1-7. |
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| Authors: | LI Tai-yu ZHANG Yu-lin |
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| Institution: | 1. Shanghai Academy of Spaceflight Technology, Shanghai 200233, China; 2. Jiuquan Satellite Launch Center, Jiuquan Gansu 732750, China |
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| Abstract: | According to the direction and damping characteristic of magnetic torque and the theory of linearity,the control scheme of three axis attitude stabilization for micro-satellite just using magnetic torque was presented in this paper.The attitude kinetic equation of micro-satellite and its improved form were also derived.The theory analysis and simulation results showed that the control law in this paper was simple,which would provide the improved attitude precision. |
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| Keywords: | Micro-satellite Attitude control Magnetorquer Additional magnetic moment Stability |
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