| 引用本文: | 张宪亮,宋婷,阳光,贺亮,袁建平,郝田蔚.组合体航天器的姿态无模型自适应控制[J].哈尔滨工业大学学报,2018,50(10):104.DOI:10.11918/j.issn.0367-6234.201709029 |
| ZHANG Xianliang,SONG Ting,YANG Guang,HE Liang,YUAN Jianping,HAO Tianwei.Model-free adaptive attitude control of assembled spacecraft[J].Journal of Harbin Institute of Technology,2018,50(10):104.DOI:10.11918/j.issn.0367-6234.201709029 |
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| 组合体航天器的姿态无模型自适应控制 |
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张宪亮1,2,宋婷1,2,阳光3,贺亮1,2,袁建平4,郝田蔚5
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(1.上海航天控制技术研究所,上海 201109;2.上海市空间智能控制技术重点实验室(上海航天控制技术研究所),上海 201109;3.上海航天技术研究院,上海 201109;4.西北工业大学 航天学院,西安 710005;5.华域汽车电动系统有限公司,上海 201109)
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| 摘要: |
| 为解决转动惯量参数未知组合体航天器的姿态精确控制问题，基于无模型自适应控制方法设计了一种不依赖于航天器精确动力学模型的组合体航天器姿态无模型自适应控制算法.首先，基于单输入单输出离散时间系统的数据驱动控制方法推导得出无模型自适应控制方程；然后，将无模型自适应控制方法拓展到组合体航天器姿态控制中，设计应用于组合体航天器姿态控制的无模型控制器；此外，为了缩短控制收敛时间，结合组合体航天器动力学特性，对姿态无模型控制器的控制过程进行优化设计；最后，以在轨服务航天器目标抓捕后的操作为研究背景进行组合体航天器的无模型自适应控制算法和无模型控制过程优化算法的数学仿真，验证了算法的有效性和可行性.数学仿真结果表明：所设计的组合体航天器无模型自适应算法有效，能够实现惯性参数未知的组合体航天器的姿态精确控制；且通过无模型控制过程优化设计，可以实现组合体航天器姿态控制过程的快速收敛；同时，该算法具有较高的控制精度.
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| 关键词: 航天器 自适应控制 组合体 姿态控制 无模型 |
| DOI：10.11918/j.issn.0367-6234.201709029 |
| 分类号:V412.4+2 |
| 文献标识码:A |
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| Model-free adaptive attitude control of assembled spacecraft |
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ZHANG Xianliang1,2,SONG Ting1,2,YANG Guang3,HE Liang1,2,YUAN Jianping4,HAO Tianwei5
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(1.Shanghai Aerospace Control Technology Institute, Shanghai 201109, China; 2. Shanghai key Laboratory of Space Intelligent Control Technology (Shanghai Aerospace Control Technology Institute), Shanghai 201109, China; 3.Shanghai Academy of Spacecraft Technology, Shanghai 201109, China; 4. School of Astronautics, Northwestern Polytechnical University, Xian 710005, China; 5.Huayu Automotive Electric Drive System Co., Ltd, Shanghai 201109, China)
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| Abstract: |
| In order deal with the attitude control of assembled spacecraft whose moment of inertia is unknown, a spacecraft combination attitude control algorithm, which is independent of accurate dynamic model, was designed based on model-free control method. Firstly, a model-free adaptive control equation was derived based on date driven control method of a single input and single output discrete-time system. Then, the model-free adaptive control method was introduced to the attitude control of the assembled spacecraft, and the model-free adaptive controller was derived. In addition, the attitude control process was optimized based on the dynamics characteristics of the combined spacecraft. Finally, the model-free adaptive control algorithm and the control process optimization algorithm were simulated under the background of the operation after target capturing. The results show that the designed model-free adaptive algorithm is feasible, and it can achieve precise control of assembled spacecraft whose inertial parameter is unknown. By optimizing the control process, fast convergence of attitude control can be achieved with a higher accuracy.
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| Key words: spacecraft adaptive control assembled spacecraft attitude control model-free |
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