| Spacecraft Dynamic Characteristics While Deploying Flexible Beams |
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| 引用本文： | 程绪铎,李俊峰,樊勇,王照林. Spacecraft Dynamic Characteristics While Deploying Flexible Beams[J]. 清华大学学报, 2002, 7(5) |
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| 作者姓名： | 程绪铎 李俊峰 樊勇 王照林 |
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| 作者单位： | CHENG Xuduo LI Junfeng，FAN Yong WANG Zhaolin Department of Engineering Mechanics，Tsinghua University，Beijing 100084，China |
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| 基金项目： | Supported by TRAPOYT(1999- 2 0 0 3 ) |
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| 摘 要： | IntroductionVibrations increase when flexible spacecraft beamsare deployed. The deploying and the vibrations ofthe beams influence the attitude motion of thespacecraft. Li and Wang[1,2 ] has studied thedynamics of a rigid body spacecraft with twosymmetric deploying flexible beams. Theapproximate formulas were given for theamplitudes of the beams and the attitude angularvelocities of the spacecraft for certain conditions.Song and Ma[3] found the dynamic equations forflexible appendages of spa…
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Spacecraft Dynamic Characteristics While Deploying Flexible Beams |
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| CHENG Xuduo LI Junfeng,FAN Yong WANG Zhaolin. Spacecraft Dynamic Characteristics While Deploying Flexible Beams[J]. Tsinghua Science and Technology, 2002, 7(5) |
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| Authors: | CHENG Xuduo LI Junfeng FAN Yong WANG Zhaolin |
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| Affiliation: | CHENG Xuduo LI Junfeng,FAN Yong WANG Zhaolin Department of Engineering Mechanics,Tsinghua University,Beijing 100084,China |
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| Abstract: | The attitude dynamic equations of a spacecraft while deploying two flexible beams and the beam equations were developed from momentum theory. The dynamic equations were solved numerically using the Runge-Kutta method to calculate the vibration amplitudes of the flexible beams and the attitude angular velocity. The results show that the vibration amplitudes increase as the beam length increases or as the initial attitude angular velocity increases. The results also show that the vibration amplitudes decrease as the deployment velocity increases. |
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| Keywords: | attitude dynamics spacecraft flexible beam |
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