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

  • 제41권9호
  • /
  • Pages.720-725
  • /
  • 2013
  • /
  • 1225-1348(pISSN)
  • /
  • 2287-6871(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
권호 표지
DOI QR코드

DOI QR Code

열선절단방식 구속분리장치를 적용한 큐브위성의 구조설계

Structural Design of Cube Satellite by Using Heating Wire Cutting Type Separation Mechanism

  • Oh, Hyun-Ung (Space Technology Synthesis Lab., Department of Aerospace Engineering, Chosun University) ;
  • Kwon, Sung-Cheol (Space Technology Synthesis Lab., Department of Aerospace Engineering, Chosun University)
  • 투고 : 2013.03.20
  • 심사 : 2013.08.22
  • 발행 : 2013.09.01
PDF 다운로드
⟨ 이전 논문 다음 논문 ⟩

초록

큐브위성에서는 일반적으로 열선 작동 시 나일론선의 절단과 함께 구속을 해제하는 메커니즘을 적용하고 있다. 이를 적용할 경우 메커니즘은 단순하여 적용이 용이하나 다수의 구조물의 구속 및 분리를 위해 다수의 열선을 적용해야 하는 등 시스템의 복잡화가 불가피하며, 나일론선의 체결력이 상대적으로 취약하여 작용하중이 큰 구조물의 구속을 통한 구조건전성 확보에 취약한 단점을 갖는다. 본 연구에서는 상기의 단점을 극복하기 위한 큐브위성용 구속분리장치와 이를 적용하여 복수구조물의 동시 구속 및 분리가 가능한 큐브위성의 구조설계를 제안하였다. 분리장치 실험실 모델의 동작시험을 통해 분리장치의 기능성을 검증하였으며, 주요 분리 대상체인 상부 및 하부 주구조체가 분리장치에 의해 동시 구속된 상태의 큐브위성의 구조해석을 통해 구조설계의 유효성을 입증하였다.

Nylon wire cutting method by nichrome wire is generally applicable for cube satellite applications due to its advantages of simplicity. However, the system complexity is not avoidable to apply it on the cube satellite with multi-deployable structures. A lower constraint force of the mechanism is also one of the disadvantages of the mechanism. In this study, we proposed a preliminary structure design of cube satellite with the separation mechanism which is applicable for holding and release of the multi-deployable structures. The effectiveness of the mechanism design was verified through function test of EM mechanism. The structure analysis results showed that the structure design proposed in this study is feasible.

키워드

참고문헌

  1. K. L. Hwang, M. I Min, B. Y Moon and Y. K. Chang "Mechanical System Design and Development of the HAUSAT-1 Picosatellite" J. of The Korean Society for Aeronautical and Space Sciences, Vol. 32, No. 9, 2004, pp. 103-113. https://doi.org/10.5139/JKSAS.2004.32.9.103
  2. H. S. Seo, J. H. Lee, S. H. Kim, K. W. Kim, C. H. Kim, J. H. Lim, S. W. Kim, S. H. Kim, D. S. Hwang, J. W. Lee and E. S. Han "Analysis On Nano or Pico-Satellite System Design Technologies" J. of the Korean Society for Aeronautical & Space Sciences Fall Conference, May. 2012, pp. 1033-1036.
  3. K. Konoue, and S. Matsunaga, "A Development Summary of CUTE-I: Titech CubeSat 2001" Proc. the 45th Space Sciences and Technology Conference, Hamamatsu, Japan, October 2001, pp. 801-806.
  4. S. H. Kim, J. Y Kim, T. Y. Kong, J. H. Park and S. I. Jeong "Design and Manufacturing Process of Nanosatellite SNUSAT-1 Prototype" J. of the Korean Society for Aeronautical & Space Sciences Fall Conference, May. 2012, pp. 1093-1096.
  5. Y. S. Lee, H. Jin, J. H. Sun, G. H. Kim, D. H. Lee, G. David and P. Robert "Mechanical Design of STEIN for Kyung Hee CINEMA" J. of the Korean Society for Aeronautical & Space Sciences Fall Conference, May, 2010, pp. 467-470.
  6. J. R. Jung, G. I. Kim, S. J Lee and C. H. Kang "Characteristics of the Shock Response Spectrum for Structures Subjected to Pyroshock" J. of the Korean Society for Aeronautical & Space Sciences Fall Conference, May, 2011, pp. 940-946.
  7. H. Sawada, and S. Matsunaga "A Development of Mechanism and Structure of TITech Cubesat CUTE-I and Environment Test" Proc. the 45th Space Sciences and Technology Conference, Hamamatsu, Japan, October 2001, pp. 807-812.
  8. W. Miyazawa, and I. Morita "Tokyo Tech Pico-Satellite CUTE-II: Missions and Concept Design" Society for Aeronautical and Space Science, Tokyo, Japan, Vol.24, 2004, pp. 1136-1141.
  9. S. Y. Jeong, H. U. Oh, K. J. Lee, B. S. Kim, "Mechanical Stability Analysis of PCB and Component for Launch and On-orbit Environment" J. of The Korean Society for Aeronautical and Space Sciences, Vol. 39, No. 10, September, 2011, pp. 952-958. https://doi.org/10.5139/JKSAS.2011.39.10.952

피인용 문헌

  1. Performance Verification of Hinge Driving Segmented Nut Type Holding and Release Mechanism for Cube Satellite Applications vol.42, pp.6, 2014, https://doi.org/10.5139/JKSAS.2014.42.6.529
  2. Launch and On-orbit Environment Verification Test of Flight Model of Hinge Driving Type Holding and Release Mechanism based on the Burn Wire Release vol.44, pp.3, 2016, https://doi.org/10.5139/JKSAS.2016.44.3.274