| 可变构型复合柔性结构航天器动力学建模研究 |
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| 引用本文： | 史纪鑫,曲广吉.可变构型复合柔性结构航天器动力学建模研究[J].宇航学报,2007,28(1):130-135. |
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| 作者姓名： | 史纪鑫 曲广吉 |
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| 作者单位： | 中国空间技术研究院总体部,北京,100094 |
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| 基金项目： | 解放军总装备部预研项目 |
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| 摘 要： | 针对中心刚体加复合柔性结构类航天器采用混合坐标法和子结构模态综合法，建立了可变构型复合柔性结构航天器低阶动力学模型。获得的柔性动力学方程及其各类耦合系数矩阵，适用于全星级可变构型系统和部件级复合柔性附件系统的控制系统设计与仿真，该模型具有阶数低和工程实用的特点。
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| 关 键 词： | 航天器 柔性航天器动力学 模态综合 混合坐标法 |
| 文章编号： | 1000-1328（2007）01-0130-06 |
| 修稿时间： | 2006-04-032006-07-03 |
Mathematical Modeling of a Class of Variable Structure Spacecraft with Flexible Multibody Appendages |
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| SHI Ji-xin,QU Guang-ji.Mathematical Modeling of a Class of Variable Structure Spacecraft with Flexible Multibody Appendages[J].Journal of Astronautics,2007,28(1):130-135. |
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| Authors: | SHI Ji-xin QU Guang-ji |
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| Institution: | China Academy of Space Technology, Beijing 100094, China |
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| Abstract: | A low order mathematical model for a class of flexible multibody spacecraft is obtained by hybrid coordinate and component mode synthesis. The generic spacecraft considered consists of a main rigid body to which a number of flexible muhibody appendages are attached. The model and flexible coupling coefficients developed can be used for analysis and simulation of many realistic spacecrafts. The model is low-order and adapts to control system design for this kind of variable structure spacecraft. |
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| Keywords: | Spacecraft Flexible spacecraft dynamic Mode synthesis Hybrid coordinate |
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