Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Falcon 9 Type Korean RLV and GTO-LV Mission Design

Falcon 9 방식의 한국형 재사용 발사체 및 정지궤도 발사체 임무설계

  • Lee, Keum-Oh (Small Launcher R&D Program Office, Korea Aerospace Research Institute) ;
  • Seo, Daeban (Small Launcher R&D Program Office, Korea Aerospace Research Institute) ;
  • Lim, Byoungjik (Small Launcher R&D Program Office, Korea Aerospace Research Institute) ;
  • Lee, Junseong (Small Launcher R&D Program Office, Korea Aerospace Research Institute) ;
  • Park, Jaesung (Small Launcher R&D Program Office, Korea Aerospace Research Institute) ;
  • Choi, Sujin (Small Launcher R&D Program Office, Korea Aerospace Research Institute) ;
  • Lee, Keejoo (Small Launcher R&D Program Office, Korea Aerospace Research Institute)
  • Received : 2022.05.31
  • Accepted : 2022.06.21
  • Published : 2022.06.30
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Abstract

The strategy to develop a launch vehicle family by bundling multiple rocket engines of a single type has been proven by SpaceX and their reusable fleet comprised of Falcon 9 and Falcon Heavy. In this study, we revisit a potential launch vehicle family out of a 35 tonf-class methalox staged combustion cycle engine and evaluate their utility and performance in various space missions. For example, a Korean version of Falcon 9 can deliver 4.7 tons of payload into 500 km SSO in an expendable mode while the payload is reduced to 2.16 tons in a sea-landing reusable mode. A Korean version of Falcon Heavy can deliver 4.4 tons into GTO when launched from the Naro Space Center, indicating that this common booster core configuration can handle Cheollian 2 albeit the high inclination. Once developed, the same methaloax engine can power the first-stage of smallsat launch vehicles and air launch vehicles.

한가지 유형의 엔진 여러 개를 번들로 묶어서 발사체 제품군을 개발하는 전략은 SpaceX와 그들의 재사용 발사체 Falcon 9과 Falcon Heavy에 의해 입증되었다. 이 연구에서 우리는 35톤급 메탄 다단 연소 사이클 엔진을 이용한 잠재적인 발사체 제품군을 제시하였으며, 다양한 우주 임무에서 그것들의 유용성과 성능을 평가하였다. 예를 들어, Falcon 9의 한국형 버전은 소모성 모드에시 500 km SSO에 약 4.7톤의 탑재체를 투입할 수 있는 반면에, 해상에 착륙하는 모드에서는 약 2.16톤의 탑재량으로 줄어들게 된다. Falcon Heavy의 한국형 버전은 나로우주센터에서 발사되었을 때, 4.4톤을 GTO에 투입할 수 있으며, 이는 이 공통부스터코어 구성이 높은 경사각에도 불구하고 천리안 2호 위성을 투입할 수 있는 것으로 나타났다. 개발 후, 이 메탄 엔진이 소형위성 발사체에 추력공급 용도로도 사용도 가능하다.

Keywords

Acknowledgement

본 논문은 한국항공우주연구원의 미래기술 전략수립 워킹그룹의 활동의 후속으로 미래발사체 재사용을 위한 요소기술 선행연구 과제의 결과로 수행되었습니다.

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