DYNAMIC PROPERTY ANALYSIS FOR SPACECRAFT WITH BEAM-LIKE DEPLOYING APPENDAGES

Zhu Gui-dong; Wang Beng-li; Shao Cheng-xun

doi:10.11728/cjss1996.04.326

Volume 16 Issue 4

Dec. 1996

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Article Navigation > Chinese Journal of Space Science > 1996 > 16(4): 326-330

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, 16(4): 326-330. doi: 10.11728/cjss1996.04.326

Citation:

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, 16(4): 326-330. doi: 10.11728/cjss1996.04.326

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DYNAMIC PROPERTY ANALYSIS FOR SPACECRAFT WITH BEAM-LIKE DEPLOYING APPENDAGES

doi: 10.11728/cjss1996.04.326 cstr: 32142.14.cjss1996.04.326

Department of Astronautics and Mechanics, Harbin Institute of Technology, 150001

Received Date: 1995-10-26
Rev Recd Date: 1996-03-14
Publish Date: 1996-12-24

Abstract

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.
- Spacecraft dynamics,
- Deploying,
- Flexible appendages