| 基于中心流形理论的欠驱动航天器姿态控制 |
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| 引用本文： | 王艺,戈新生.基于中心流形理论的欠驱动航天器姿态控制[J].北京机械工业学院学报,2010,25(2):37-40,48. |
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| 作者姓名： | 王艺 戈新生 |
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| 作者单位： | 北京信息科技大学自动化学院,北京,100192 |
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| 基金项目： | 国家自然科学基金项目 |
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| 摘 要： | 考虑一类欠驱动航天器的执行机构为喷气推力器,根据航天器姿态动力学理论,建立欠驱动航天器姿态动力学方程。对于仅有两个反作用飞轮的零动量姿态控制系统设计了不连续的状态反馈控制器。基于给出的欠驱动航天器姿态动力学方程,设计控制律,利用中心流形方法判别驱动航天器系统在临界情形下的稳定性,得出欠驱动航天器姿态达到稳定状态的稳定性控制参数条件。数值仿真验证了所设计控制律的有效性。
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| 关 键 词： | 欠驱动航天器 姿态稳定 控制 中心流形 |
Attitude control Of an underactuated spacecraft base on center manifold theory |
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| WANG Yi,GE Xin-sheng.Attitude control Of an underactuated spacecraft base on center manifold theory[J].Journal of Beijing Institute of Machinery,2010,25(2):37-40,48. |
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| Authors: | WANG Yi GE Xin-sheng |
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| Affiliation: | (School of Automation,Beijing Information Science and Technology University,Beijing 100192,China) |
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| Abstract: | Considering a class of underactuated spacecraft executing agency as the jet thruster,according to spacecraft attitude dynamics theory,underactuated spacecraft attitude dynamics equations are set up.Discrete state feedback controller is designed for zero-momentum attitude control system with only two reaction wkeels.Based on the given underactuated spacecraft attitude dynamics equations,control laws,using the center manifold method,the drive spacecraft system stability in critical situations is discriminated.The stability control parameters of underactuated spacecraft are figured out under steady state conditions.Numerical simulation shows the effectiveness of the designed control law. |
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| Keywords: | underactuated spacecraft attitude stablity control center manifold |
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