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

  • 제44권3호
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  • Pages.274-280
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  • 2016
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  • 1225-1348(pISSN)
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  • 2287-6871(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
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열선분리방식을 이용한 힌지구동형 구속분리장치 비행모델의 발사 및 궤도환경 검증시험

Launch and On-orbit Environment Verification Test of Flight Model of Hinge Driving Type Holding and Release Mechanism based on the Burn Wire Release

  • Lee, Myeong-Jae (Space Technology Synthesis Lab, Dept. of Aerospace Engineering, Chosun University) ;
  • Lee, Yong-Keun (Optronics System Group, Hanwha Thales) ;
  • Kang, Suk-Joo (Optronics System Group, Hanwha Thales) ;
  • Oh, Hyun-Ung (Space Technology Synthesis Lab, Dept. of Aerospace Engineering, Chosun University)
  • 투고 : 2015.06.06
  • 심사 : 2016.02.16
  • 발행 : 2016.03.01
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초록

2015년 발사예정인 우주기반기술 검증용 큐브위성 STEP Cube Lab.의 주요 탑재체인 열선절단방식 힌지구동형 구속분리장치는 높은 체결력 및 저충격 구현의 장점으로 초소형위성 전개구조물의 구속/분리에 적용이 용이하며, 기존 나일론선 절단방식의 낮은 체결력 및 복수구조물 적용에 따른 시스템 복잡화의 단점을 극복가능하다. 본 논문에서는 인증모델 검증시험이 완료된 구속분리장치의 궤도검증 임무수행을 목적으로 체결력 검증 및 전개 확인 신호 획득이 가능한 비행모델을 설계/제작하였으며, 탑재체 레벨에서의 발사 및 궤도환경 검증시험을 수행하여 설계 유효성을 입증하였다.

Hinge driving type holding and release mechanism based on the burn wire release for application of cubesat is main payload of STEP Cube Lab. (Cube Laboratory for Space Technology Experimental Project) to be launched at 2015. It has high constraint force, low shock level as well as surmounting drawbacks of conventional nichrome burn wire release method that has relatively low constraint force and system complexity for application of multi-deployable systems. In this paper, we have proposed a flight model of holding and release mechanism for the verification of the constraint force and deployment status signal acquisition. To validate the effectiveness of the flight model, launch and on-orbit environment verification test have been performed.

키워드

참고문헌

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