| 航天器自主姿态控制的正规矩阵设计方法 |
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| 引用本文： | 朱宏玉,崔平远,崔祜涛.航天器自主姿态控制的正规矩阵设计方法[J].吉林大学学报(工学版),2008(Z2). |
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| 作者姓名： | 朱宏玉 崔平远 崔祜涛 |
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| 作者单位： | 哈尔滨工业大学深空探测基础研究中心; |
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| 基金项目： | “863”国家高技术研究发展计划项目(2004AA735080)． |
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| 摘 要： | 为满足航天器自主系统的在轨重设计及对重设计结果进行评估的要求,研究了姿态动力学自然特性以及基于结构特性的姿态控制设计方法。证明了挠性航天器姿态动力学传递函数矩阵的正规性,并对惯量矩阵的对角优势性进行了分析。将这两个特性应用于姿态控制设计,分别得到了乘性摄动和逆加摄动不确定性描述下的鲁棒稳定条件。给出了姿态控制的正规矩阵设计方法,而且设计结果的鲁棒性容易检验,适合在自主航天器中应用。对这两种鲁棒稳定条件的比较表明,逆加摄动下的结果可以更好地兼顾各回路的性能要求。
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| 关 键 词： | 飞行器控制、导航技术 航天器姿态控制 正规矩阵方法 自主控制 鲁棒控制 对角优势 惯量张量 反馈摄动 |
Normal matrix design method for autonomous attitude control of spacecrafts |
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| ZHU Hong-yu CUI Ping-yuan CUI Hu-tao.Normal matrix design method for autonomous attitude control of spacecrafts[J].Journal of Jilin University:Eng and Technol Ed,2008(Z2). |
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| Authors: | ZHU Hong-yu CUI Ping-yuan CUI Hu-tao |
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| Affiliation: | Deep Space Exploration Research Center;Harbin Institute of Technology;Harbin 150080;China |
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| Abstract: | The natural properties of spacecraft attitude dynamics and the methed for the design of attitude control based on natural properties were investigated for the in-orbit redesign and evaluation of the redesigned result in autonomous spacecraft systems.The transfer function matrix of the flexible spacecraft was shown to be a normal matrix.Then diagonal dominance property of the inertia matrix was also analyzed.With the application of the above-mentioned two properties in the design of attitude control,robust s... |
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| Keywords: | control and navigation technology of aerocraft spacecraft attitude control normal matrix approach autonomous control robust control diagonal dominance inertia tensor feedback perturbation |
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