Design, Test and Verification of Small Satellite Solar Wings

Paper number

IAC-08.B4.6.B9

Author

Dr. Wei Wang, DFH Satellite Co. Ltd., China

Coauthor

Mr. Zhaoguang Bai, China

Year

2008

Abstract

Generally, the small satellite solar wing is mainly made up of SAD (solar array driver) mechanism, panels, solar cells, deployment mechanism, harness and some other elements. The deployment mechanism is one typical one-shot device, and the SAD is a continuously operating device. Unfortunately, the general requirements for deployment mechanism, namely deploy safely, shall lead to high loads and high torques and these loads are very hostile to SADs. Moreover, such loads will reduce the reliability or even cause some failures of SADs.
    This paper put forward a new method to verify the design of small satellite solar wings. The method is helpful to increase deployment safety and reliability of SADs. At first, dynamics model of the solar wing deployment and the verification strategy of solar wing are introduced. Then test and analysis method to get data is put forward. Finally, an example is illustrated.

Abstract document

IAC-08.B4.6.B9.pdf

Manuscript document

IAC-08.B4.6.B9.pdf (🔒 authorized access only).

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