| 柔性航天器自由飞行状态系统基频的估算方法 |
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| 引用本文： | 徐小胜,于登云,曲广吉.柔性航天器自由飞行状态系统基频的估算方法[J].宇航学报,2004,25(2):208-212. |
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| 作者姓名： | 徐小胜 于登云 曲广吉 |
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| 作者单位： | 中国空间技术研究院总体设计部,北京,100086 |
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| 摘 要： | 首先分别采用部件模态和系统模态建立柔性航天器在轨运行状态下的动力学方程；重点推导了航天器系统模态与其部件模态之间的模态恒等式，得到了由部件模态计算系统模态频率的一般公式；然后结合目前航天器的常见构型，对一般公式进行合理简化，得到了估算航天器系统基频的简化公式；最后给出了简化公式的工程应用算例。
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| 关 键 词： | 柔性航天器 部件模态 系统模态 惯性完备性 模态恒等式 |
| 文章编号： | 1000-1328(2004)02-0208-05 |
The natural frequency calculating for flexible spacecraft in free flight |
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| XU Xiao-sheng,YU Deng-yun,QU Guang-ji.The natural frequency calculating for flexible spacecraft in free flight[J].Journal of Astronautics,2004,25(2):208-212. |
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| Authors: | XU Xiao-sheng YU Deng-yun QU Guang-ji |
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| Abstract: | The calculation of the natural frequencies of flexible spacecraft was studied.First,the dynamical model of flexible spacecraft was formulated using appendage modes and system modes respectively.Second,the modal identity between appendage modes and system modes was deduced by which the natural frequencies of flexible spacecraft can be calculated.Finally,Considering the normal framework of modern spacecraft,the identity was simplified and the estimating formula for its basic natural frequency was got.The formula is simple and practical,and it shows the contribution of each appendage to the basic frequency of flexible spacecraft. |
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| Keywords: | Flexible spacecraft Appendage mode System mode Inertial completeness Model identity |
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