Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Conceptual Design of a LOX/Methane Rocket Engine for a Small Launcher Upper Stage

소형발사체 상단용 액체메탄 로켓엔진의 개념설계

  • Kim, Cheulwoong (Small Launcher R&D Office, Korea Aerospace Research Institute) ;
  • Lim, Byoungjik (Small Launcher R&D Office, Korea Aerospace Research Institute) ;
  • Lee, Junseong (Small Launcher R&D Office, Korea Aerospace Research Institute) ;
  • Seo, Daeban (Small Launcher R&D Office, Korea Aerospace Research Institute) ;
  • Lim, Seokhee (Small Launcher R&D Office, Korea Aerospace Research Institute) ;
  • Lee, Keum-Oh (Small Launcher R&D Office, Korea Aerospace Research Institute) ;
  • Lee, Keejoo (Small Launcher R&D Office, Korea Aerospace Research Institute) ;
  • Park, Jaesung (Small Launcher R&D Office, Korea Aerospace Research Institute)
  • Received : 2022.06.02
  • Accepted : 2022.08.15
  • Published : 2022.08.31
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Abstract

A 3-tonf class liquid rocket engine that powers the upper stage of a small launcher and lifts 500 kg payload to 500 km SSO is designed. The small launcher is to utilize the flight-proven technology of the 75-tonf class engine for the first stage. A combination of liquid oxygen and liquid methane has been selected as their cryogenic states can provide an extra boost in specific impulse as well as enable a weight saving via the common dome arrangement. An expander cycle is chosen among others as the low-pressure operation makes it robust and reliable while a specific impulse of over 360 seconds is achievable with the nozzle extension ratio of 120. Key components such as combustion chamber and turbopump are designed for additive manufacturing to a target cost. The engine system provides an evaporated methane for the autogenous pressurization system and the reaction control of the stage. This upper stage propulsion system can be extended to various missions including deep space exploration.

500 kg의 페이로드를 500 km 태양동기궤도에 이송가능한 소형발사체의 상단에 사용될 3톤급 액체로켓엔진을 설계하고 있다. 소형발사체의 1단에는 비행시험으로 검증된 75톤급 엔진을 사용한다. 상단용 엔진은 액체산소와 액체메탄을 연료로 사용되는데, 이 추진제 조합은 공통격벽탱크를 적용하여 무게 감소가 가능하고 비추력도 높다. 상단엔진의 사이클로는 저압으로 운용되어 신뢰성이 높은 팽창식 사이클을 채택했으며, 노즐 확대비 120이상에서 360초를 상회하는 비추력 성능을 보일 것으로 평가되었다. 엔진의 주요구성품인 연소기와 터보펌프는 목표 비용을 맞추기 위하여 적층제조된다. 엔진은 자가증기가압과 롤추력제어를 위하여 가열된 증기메탄을 제공하고, 이러한 기능을 가진 상단 추진기관시스템은 심우주탐사 등 다양한 임무에 확대 적용 가능할 것으로 기대된다.

Keywords

Acknowledgement

본 연구는 한국항공우주연구원의 2단형 소형발사체선행기술개발사업(FR22B00)과 한국연구재단(과학기술정보통신부)의 스페이스챌린지사업(2021M1A3B807777112)의 지원을 받아 수행되었습니다.

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