| 带挠性附件的航天器结构-姿态耦合动力学 |
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| 引用本文： | 王钦,何星星,文援兰.带挠性附件的航天器结构-姿态耦合动力学[J].上海航天,2011,28(2):12-16,49. |
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| 作者姓名： | 王钦 何星星 文援兰 |
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| 作者单位： | 1. 国防科学技术大学航天与材料工程学院,湖南长沙410073;上海卫星工程研究所,上海200240
2. 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： | 用Lagrange方程建立了基于混合坐标法的带挠性附件航天器结构-姿态动力学模型,对挠性附件结构的振动特性及其与航天器的耦合关系进行了理论分析,提出了航天器结构-姿态联合仿真分析的方法,并以某卫星天线为挠性附件结构,仿真分析了天线结构的振动特性及其对姿态控制系统的影响.结果表明:提出的航天器结构-姿态联合仿真方法能有效...
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| 关 键 词： | 挠性附件 姿态控制 振动特性 联合仿真 |
Spacecraft Structures-Attitude Coupling Dynamics with Flexible Appendages |
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| WANG Qin,HE Xing-xing,WEN Yuan-lan.Spacecraft Structures-Attitude Coupling Dynamics with Flexible Appendages[J].Aerospace Shanghai,2011,28(2):12-16,49. |
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| Authors: | WANG Qin HE Xing-xing WEN Yuan-lan |
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| Institution: | WANG Qin1,2,HE Xing-xing1,WEN Yuan-lan1(1.College of Aerospace and Material Engineering,NUDT,Changsha Hunan 410073,China,2.Shanghai Institute of Satellite Engineering,Shanghai 200240,China) |
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| Abstract: | Based on coupling dynamics of the spacecraft structure and attitude with flexible appendages,the structure and attitude model of the spacecraft was established with Lagrange equations using hybrid coordinate method in this paper.The coupling relation between the flexible structure and spacecraft body was analyzed in theory.And the co-simulation method of spacecraft structure and attitude was put forward.The vibration characteristics of flexible structure were analyzed in finite element method,and so was the... |
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| Keywords: | Flexible appendages Attitude control Vibration characteristic Co-simulation |
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