| 基于混杂系统的空间飞行器悬停控制 |
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| 引用本文： | 薛白,佘志坤,余婧,刘铁钢,郑志明.基于混杂系统的空间飞行器悬停控制[J].中国空间科学技术,2010,30(2). |
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| 作者姓名： | 薛白 佘志坤 余婧 刘铁钢 郑志明 |
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| 作者单位： | 北京航空航天大学数学与系统科学学院,北京,100191 |
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| 摘 要： | 基于空间飞行器的轨道动力学原理,利用混杂系统模型研究了悬停轨道问题,建立了悬停轨道的混杂系统模型;借此模型,针对目标星轨道为椭圆的情况,提出了等距离悬停轨道控制和椭圆悬停轨道控制两种方案,分别推导出在这两种方案下对悬停星所施加的控制力。数值仿真结果表明,分别对悬停星施加相应的控制力,能够实现对目标星的悬停。
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| 关 键 词： | 混杂系统 悬停轨道 轨道控制 数值仿真 航天器 |
Control on the Spacecraft Hovering Based on Hybrid Systems |
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| Xue Bai,She Zhikun,Yu Jing,Liu Tiegang,Zheng Zhiming.Control on the Spacecraft Hovering Based on Hybrid Systems[J].Chinese Space Science and Technology,2010,30(2). |
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| Authors: | Xue Bai She Zhikun Yu Jing Liu Tiegang Zheng Zhiming |
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| Institution: | Xue Bai She Zhikun Yu Jing Liu Tiegang Zheng Zhiming(School of Mathematics , Systems Science,Beihang University,Beijing 100191) |
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| Abstract: | Based on the dynamical principle of spacecraft orbits,the hybrid system model was used to study the hovering problems and a hybrid system model of hovering orbits was established.Based on this model,in the case that the target satellite orbit is elliptic,an equidistant hovering orbit control scheme and an elliptical hovering orbit control scheme were proposed,and the corresponding forces exerted on the hovering satellite for these two schemes were derived respectively.Numerical simulation results showed tha... |
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| Keywords: | Hybrid systems Hovering orbits Orbit control Numerical simulation Spacecraft |
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