Journal of the Korean Society for Aeronautical & Space Sciences (한국항공우주학회지)

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Preliminary System Design of STEP Cube Lab. for Verification of Fundamental Space Technology

우주기반기술 검증용 극초소형 위성 STEP Cube Lab.의 시스템 개념설계

  • 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)
  • Received : 2014.01.17
  • Accepted : 2014.02.28
  • Published : 2014.05.01
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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.

본 논문에서 제안한 우주기반기술 검증용 극초소형 위성의 명칭은 STEP Cube Lab.(Cube Laboratory for Space Technology Experimental Project)이며, 주요임무는 가변 방사율 열제어기, 형상기억합금 진동 절연기, 진동형 히트파이프, MEMS 기반 고체 추력기와 같이 국내 산학연에서 기 수행된 우주핵심기술을 발굴 및 탑재하여 궤도검증을 실시하는 것이다. 또한, 배열형 집광렌즈가 적용된 고효율 집광형 태양전력시스템과 열선절단방식이 적용되어 높은 체결력과 적용방법에 따라 복수구조물의 구속 및 분리가 가능한 무충격 구속분리장치를 주요 탑재체로 개발하여 궤도 검증을 실시예정이다. 본 논문에서는 상기 탑재체의 궤도 검증을 임무목적으로 하는 STEP Cube Lab.의 체계 및 부체계 개념설계를 통해 임무의 구현 가능성을 검토하였다.

Keywords

References

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