Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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A Preliminary Configuration Design of Methane/Oxygen Bipropellant Small-Rocket-Engine through Theoretical Performance Analysis

이론성능해석에 의한 메탄/산소 이원추진제 소형로켓엔진의 예비형상설계

  • Bae, Seong Hun (Department of Mechanical Engineering, Pukyong National University) ;
  • Jung, Hun (Department of Mechanical Engineering, Graduate School, Pukyong National University) ;
  • Kim, Jeong Soo (Department of Mechanical Engineering, Pukyong National University)
  • Received : 2015.04.11
  • Accepted : 2015.05.11
  • Published : 2015.06.01
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Abstract

Design parameters required for Methane/oxygen bipropellant small-rocket-engine were derived through a theoretical performance analysis. The theoretical performance of the rocket engine was analyzed by using CEA and optimal propellant mixture ratio, characteristic length, and optimal expansion ratio were calculated by assuming chemical equilibrium. A coaxial-type swirl injector was chosen because of its outstanding atomization performance and high combustion efficiency compared to other types of injector and also a bell nozzle with 80% of its full length was designed. The rocket engine configuration with 1.72 MPa of chamber pressure, 0.18 kg/s in total propellant mass flow, and O/F ratio of 2.7 was proposed as a ground-firing test model.

이론성능해석을 통하여 메탄/산소 이원추진제 소형로켓엔진의 형상설계에 필요한 설계인자들을 도출하였다. 로켓엔진의 이론성능 분석을 위해 CEA를 이용하였고, 추력실 내부의 화학반응을 화학평형 상태로 가정하여 엔진의 형상설계에 필요한 최적의 추진제 혼합비, 특성길이, 최적 팽창비 등을 도출하였다. 인젝터의 경우, 미립화 성능이 우수하고, 다른 인젝터 형상에 비해 연소효율이 높은 스월 동축 인젝터를 설계하였다. 노즐형상은 80%의 길이를 갖는 벨형 노즐을 설계하였고, 추력실 내부압력 1.72 MPa, 총 추진제 질량유량 0.18 kg/s, O/F ratio 2.7일 때의 지상연소시험용 로켓엔진의 형상설계 결과를 제시한다.

Keywords

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