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http://dx.doi.org/10.5139/JKSAS.2018.46.10.867

Functional Verification of Nylon Wire Cutting-Type Holding & Release Mechanism for 6U CubeSat's Solar Panel  

Park, Yeon-Hyeok (Department of Aerospace Engineering, Chosun University)
Go, Ji-Seong (Department of Aerospace Engineering, Chosun University)
Chae, Bong-Geon (Department of Satellite System, Dream Space World)
Lee, Seong-Ho (Department of Satellite System, Dream Space World)
Oh, Hyun-Ung (Department of Aerospace Engineering, Chosun University)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.46, no.10, 2018 , pp. 867-875 More about this Journal
Abstract
Conventional nylon wire cutting-type holding and release mechanisms (HRMs) are limited to securely hold the solar panel under launch environment as the size of the panel increases because the nylon wire is tightened directly on the surface of the solar panel. In this study, we proposed a nylon wire cutting-type HRM for 6U CubeSat's solar panel applying elliptic-shaped bracket with a Ball & Socket interface. The proposed HRM has the advantage of higher holding capability along in-plane and out-of plane directions of solar panel and simplicity in tightening process of nylon wire. The design drivers of structural design of CubeSat's solar panel with the proposed HRM were defined by structural analysis under launch loads. In addition, The design effectiveness of the proposed HRM was verified through the functional tests according to the thickness of nylon wire and the number of wire winding under various temperature conditions.
Keywords
CubeSat; Holding and Release Mechanism; Solar Panel; Nylon Wire;
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