| 带挠性附件航天器刚柔耦合动力学 |
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| 引用本文： | 蒋建平,李东旭.带挠性附件航天器刚柔耦合动力学[J].上海航天,2005,22(5):24-27. |
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| 作者姓名： | 蒋建平 李东旭 |
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| 作者单位： | 国防科学技术大学,航天与材料工程学院,湖南,长沙,410073 |
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| 摘 要： | 针对有板式挠性附件的航天器，根据几何变形约束法引入有限元方法，用Lagrange方程建立系统的刚柔耦合一次近似动力学方程组。在动力学方程中获得了与大范围刚体运动有关的动力刚度项。仿真结果表明，在柔性体大范围运动时动力刚度项的影响较大，忽略动力刚度项的传统动力学建模方法会给出错误结论。
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| 关 键 词： | 航天器 挠性附件 刚柔耦合 动力刚化 有限元法 |
| 文章编号： | 1006-1630（2005）05-0024-04 |
| 收稿时间： | 2004-12-13 |
| 修稿时间： | 2005-04-03 |
Study on Rigid-Flexible Coupling Dynamics of Spacecraft with Flexible Appendage |
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| JIANG Jian-ping,LI Dong-xu.Study on Rigid-Flexible Coupling Dynamics of Spacecraft with Flexible Appendage[J].Aerospace Shanghai,2005,22(5):24-27. |
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| Authors: | JIANG Jian-ping LI Dong-xu |
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| Institution: | College of Aerospace and Material Engineering, NUDT, Changsha Hunan 410073, China |
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| Abstract: | The rigid-flexible dynamics of spacecraft with board flexible appendage was studied in this paper. The dynamic equations, which included the dynamic stiffness terms with overall motions, were derived through the Lagrange methods and the finite element method. The results of numerical simulation showed that the dynamic stiffness terms had the important role when the flexible body moved in large scope. The traditional dynamic equations which neglected the dynamic stiffness terms would give the wrong conclusion for the flexible plate undergoing large overall motions. |
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| Keywords: | Spacecraft Flexible appendage Rigid-flexible coupling Dynamic stiffening Finite element method |
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