Drag Braking of the Deployment Mechanism of Solar Array on a Small Satellite | ||||
| International Conference on Aerospace Sciences and Aviation Technology | ||||
| Article 111, Volume 15, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 15 – May 28 - 30, 2013, May 2013, Page 1-16 PDF (1.09 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/asat.2013.22260 | ||||
 View on SCiNiTO | ||||
| Authors | ||||
| M. G. El-Sherbiny1; A. A. Khattab1; M. K. Kassab2 | ||||
| 1Prof. of Machine Design and Engineering Tribology, Cairo University, Egypt. | ||||
| 2Head of Structure Department, National authority for Remote Sensing and Space Sciences (NARSS), Egypt. | ||||
| Abstract | ||||
| This paper demonstrates Mechanical Desktop modelling and Finite Element Analysis of shoe brake specially designed to apply drag braking on the deployment mechanism of solar array mounted on a small satellite. Strength analysis was performed under realistic loads to the brake assembly, and the most critical points are checked. Several finite element analysis models were considered to verify the integrity of the deployment mechanism. These analyses considered the static, modal and random vibration testing to verify the safe performance of the brake after orbit insertion. | ||||
| Keywords | ||||
| Satellite; Deployment Mechanism; Brake Shoe; Solar Array; Finite Element Analysis; Modal analysis; Random analysis | ||||
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