Journal of Space Technology and Applications (우주기술과 응용)

The Korean Space Science Society (한국우주과학회)
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Development of Drag Augmentation Device for Post Mission Disposal of Nanosatellite

초소형위성의 폐기 기동을 위한 항력 증대 장치 개발

  • 김지석 (과학기술연합대학원대학교) ;
  • 김해동 (과학기술연합대학원대학교)
  • Received : 2022.01.06
  • Accepted : 2022.02.03
  • Published : 2022.02.28
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Abstract

In this paper, we described the development of a drag augmentation device for nanosatellite. Recently, space industry has entered the New Space era, and barriers to entry into Low Earth Orbit (LEO) for artificial objects such as small rockets and nanosatellite mega constellations have been significantly lowered. As a result, the number of space debris is increasing exponentially, and it is approaching as a major threat to satellite currently in operation as well as satellites to be launched in near future. To prevent this, international organizations like Inter-Agency Space Debris Coordination Committee (IADC) have been proposed space debris mitigation guidelines. The Korea Aerospace Research Institute (KARI) conducted KARI Rendezvous & Docking demonstration SATellite (KARDSAT) project, the first nanosatellites for rendezvous and docking technology demonstration in Korea, and we also developed drag augmentation device for KARDSAT Target nanosatellite that complied with the international guideline of post-mission disposal.

본 논문에서는 초소형위성용 항력 증대 장치 개발에 대해 기술하였다. 최근 우주 개발이 New Space 시대에 접어들며, 소형 로켓 및 초소형위성 거대 군집 운용 등 인공물체의 저궤도 진입 장벽이 상당히 낮아지는 추세이다. 이로 인해 우주 환경에 존재하는 우주쓰레기의 수가 기하급수적으로 늘어나고 있으며, 현재 운용중인 인공위성뿐만 아니라 앞으로 발사될 인공위성들에 큰 위협으로 다가오고 있다. 이를 방지하기 위해 국제적으로 우주쓰레기 경감 대책을 제시하고 있으며, 대표적으로 IADC(Inter-Agency Space Debris Coordination Committee)에서는 '25년 가이드라인'을 권고하고 있다. 한국항공우주연구원에서는 국내 최초로 랑데부/도킹 기술검증용 초소형위성인 KARDSAT(KARI Rendezvous & Docking demonstration SATellite) 프로젝트를 진행하였으며, KARDSAT 위성의 임무 후 폐기 기동(post-mission disposal)을 위한 항력 증대 장치 개발을 통해 우주쓰레기에 대한 국제적 가이드라인을 준수하고자 하였다.

Keywords

Acknowledgement

본 연구는 한국항공우주연구원의 기본사업으로 수행 중인 'AI기반 랑데부/도킹 기술검증용 위성 개발' 및 '궤도상 서비싱 기반기술 개발' 연구의 일부이며, 한국항공우주연구원의 지원에 감사드립니다.

References

  1. Kim HD, Recent status and future prospect on space debris mitigation guideline, J. Korean Soc. Aeronaut. Space Sci. 48, 311-321 (2020). https://doi.org/10.5139/JKSAS.2020.48.4.311
  2. Stohlman OR, Lappas V, Development of the deorbitsail flight model, in AIAA Spacecraft Structures Conference, National Harbor, MD, 13-17 Jan 2014.
  3. Taylor B, Underwood C, Viquerat A, Schenk M, Fellowes S, et al., Flight results of the InflateSail spacecraft and future applications of dragsails, in 32nd AIAA Small Satellite Conference, Logan, UT, 19 Jul 2018.
  4. Luna AG, Murbach M, Wheless J, Tanner F, The exo-brake as a de-orbit mechanism: analysis and recent flight experience through Soarex and TechEdSat flight tests, in 68th international Astronautical Congress, Adelaide, Australia, Sep 2017.
  5. Bonin G, Hiemstra J, Sears T, Zee R, The CanX-7 drag sail demonstration mission: enabling environmental stewardship for nano- and microsatellites, in 27th AIAA Conference on Small Satellites, Dubai, 1 Aug 2013.
  6. Harkness P, McRobb M, Lutzkendorf P, Milligan R, Feeney A, et al, Development status of AEOLDOS: a deorbit module for small satellites, Adv. Space Res. 54, 82-91 (2014). https://doi.org/10.1016/j.asr.2014.03.022
  7. Song SA, Kim S, Suk J, Roh JH, Development and performance test of solar sail system for CNUSAIL-1 cube satellite, J. Korean Soc. Aeronaut. Space Sci. 44, 228-239 (2016). https://doi.org/10.5139/JKSAS.2016.44.3.228
  8. Kim HD, Choi WS, Kim MK, Kim JH, Kim KD, et al., Ground test of docking phase for nanosatellite, J. Space Technol. Appl. 1, 7-22 (2021). https://doi.org/10.52912/jsta.2021.1.1.7
  9. Vallado DA, Fundamentals of Astrodynamics and Applications (McGraw-Hill, New York, NY, 2001).
  10. Underwood C, Viquerat A, Schenk M, Taylor B, Massimiani C, et al., InflateSail de-orbit flight demonstration results and follow-on drag-sail applications. Acta Astronaut. 162, 344-358 (2019). https://doi.org/10.1016/j.actaastro.2019.05.054
  11. Hoskin A, Viquerat A, Aglietti GS, Tip force during blossoming of coiled deployable booms, Int. J. Solids Struct. 118-119, 58-69 (2017). https://doi.org/10.1016/j.ijsolstr.2017.04.023
  12. Adeli SN, Deployment system for the cubesail nano-solar sail mission, Proceedings of the AIAA/USU Conference on Small Satellites, Logan, UT, 9-12 Aug 2010.
  13. Sickinger C, Herbeck L, Deployment strategies, analyses and tests for the CFRP booms of a solar sail, in European Conference on Spacecraft Structures, Materials and Mechanical Testing, CNES, Toulouse, 11-13 Dec 2002.
  14. Murphey TW, Turse D, Adams L, TRAC Boom Structural Mechanics, in 4th AIAA Spacecraft Structures Conference, Grapevine, TX, 9-13 Jan 2017.