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http://dx.doi.org/10.5139/JKSAS.2014.42.5.430

Preliminary System Design of STEP Cube Lab. for Verification of Fundamental Space Technology  

Kwon, Sung-Cheol (Space Technology Synthesis Lab., Department of Aerospace Engineering, Chosun University)
Jung, Hyun-Mo (Space Technology Synthesis Lab., Department of Aerospace Engineering, Chosun University)
Ha, Heon-Woo (Space Technology Synthesis Lab., Department of Aerospace Engineering, Chosun University)
Han, Sung-Hyun (Space Technology Synthesis Lab., Department of Aerospace Engineering, Chosun University)
Lee, Myung-Jae (Space Technology Synthesis Lab., Department of Aerospace Engineering, Chosun University)
Jeon, Su-Hyeon (Space Technology Synthesis Lab., Department of Aerospace Engineering, Chosun University)
Park, Tae-Young (Space Technology Synthesis Lab., Department of Aerospace Engineering, Chosun University)
Kang, Su-Jin (Space Technology Synthesis Lab., Department of Aerospace Engineering, Chosun University)
Chae, Bong-Gun (Space Technology Synthesis Lab., Department of Aerospace Engineering, Chosun University)
Jang, Su-Eun (Space Technology Synthesis Lab., Department of Aerospace Engineering, Chosun University)
Oh, Hyun-Ung (Space Technology Synthesis Lab., Department of Aerospace Engineering, Chosun University)
Han, Sang-Hyuk (Future Convergence Research Division, Korea Aerospace Research Institute)
Choi, Gi-Hyuk (Future Convergence Research Division, Korea Aerospace Research Institute)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.42, no.5, 2014 , pp. 430-436 More about this Journal
Abstract
The mission objective of STEP Cube Lab. (Cube Laboratory for Space Technology Experimental Project) classified as a pico-class satellite is to verify the technical effectiveness of payloads such as variable emittance radiator, SMA washer, oscillating heat pipe and MEMS based solid propellant thruster researched at domestic universities. In addition, the MEMS concentrating photovoltaic power system and the non-explosive holding and separation mechanism with the advantages of high constraint force and low shock level will be developed as the primary payloads for on-orbit verification. In this study, the feasibility of the mission actualization has been confirmed by the preliminary system design.
Keywords
Cube Satellite; Payload; MEMS; Non-explosive Holding & Separation Mechanism; Concentrating Photovoltaic Power System;
Citations & Related Records
Times Cited By KSCI : 2  (Citation Analysis)
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