| 带梁式伸展附件航天器动力学分析 |
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| 引用本文： | 朱桂东,王本利,邵成勋.带梁式伸展附件航天器动力学分析[J].空间科学学报,1996(4). |
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| 作者姓名： | 朱桂东 王本利 邵成勋 |
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| 作者单位： | 哈尔滨工业大学航天工程与力学系 |
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| 摘 要： | 带梁式伸展附件航天器动力学分析朱桂东，王本利，邵成勋（哈尔滨工业大学航天工程与力学系，１５０００１）关键词航天器动力学，伸展，柔性附件引言大型柔性可展开航天结构已被广泛地应用，并且向着大型化、轻型化、复杂化方向发展．目前可展开航天结构主要有三种：弹出...
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| 关 键 词： | 航天器动力学，伸展，柔性附件 |
DYNAMIC PROPERTY ANALYSIS FOR SPACECRAFT WITH BEAM-LIKE DEPLOYING APPENDAGES |
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| Zhu Gui-dong, Wang Beng-li, Shao Cheng-xun.DYNAMIC PROPERTY ANALYSIS FOR SPACECRAFT WITH BEAM-LIKE DEPLOYING APPENDAGES[J].Chinese Journal of Space Science,1996(4). |
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| Authors: | Zhu Gui-dong Wang Beng-li Shao Cheng-xun |
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| Abstract: | This paper studies the attitude dynamics and vibration of appendages of spacecraft with deploying appendages. A spacecraft model of a center rigid body with some deployable beams are considered. The governing equations are derived based on characteristic function of bending beam, and the effects of deploying rate and disturbance on system behavior are investigated to find the criteria of the selection of deploying rate. The numerical simulation results are also presented. |
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| Keywords: | Spacecraft dynamics Deploying Flexible appendages |
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