Effects of Clearance on Deployment of Solar Panels on Spacecraft System
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- ZHAO Yang
- Department of Astronautics Engineering, Harbin Institute of Technology
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- BAI ZhengFeng
- Department of Astronautics Engineering, Harbin Institute of Technology
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Abstract
This paper establishes a dynamics model for deploying solar panels with clearances by using a practical method and provides a useful way to identify the effects of clearances on spacecraft systems. Considering the clearance of joints, a contact dynamic model is established using the nonlinear spring-damp model and the friction effect is considered by using the Coulomb friction model. Based on the model, numeric simulation of the deployment of a single panel with clearance on a spacecraft is presented. The effects of the clearance on attitude motion of the spacecraft as well as the deployment of a solar panel with joint clearance are analyzed. The simulation results predict the effects of clearance on the attitude motion of a spacecraft system and the deployment dynamics of solar panel preferably. It is useful for engineering design of a spacecraft control system and ground text. This work provides a valuable method for improving the dynamics of spacecraft systems.
Journal
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- TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 53 (182), 291-295, 2011
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
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Details 詳細情報について
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- CRID
- 1390001204079295872
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- NII Article ID
- 10027844865
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- NII Book ID
- AA0086707X
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- ISSN
- 21894205
- 05493811
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- NDL BIB ID
- 10972271
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- Text Lang
- en
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- Data Source
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- JaLC
- NDL
- Crossref
- CiNii Articles
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- Abstract License Flag
- Disallowed