Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Pulse-mode Response Characteristics of a Small LRE for the Precise 3-axes Control of Flight Attitude in SLV

우주발사체의 비행자세 3축 정밀제어를 위한 소형 액체로켓엔진의 펄스모드 응답특성

  • 정훈 (부경대학교 대학원 에너지시스템공학과) ;
  • 김종현 (부경대학교 대학원 에너지시스템공학과) ;
  • 김정수 (부경대학교 기계공학과) ;
  • 배대석 (부경대학교 기계공학과)
  • Received : 2012.11.20
  • Accepted : 2013.01.21
  • Published : 2013.02.01
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Abstract

A liquid-monopropellant hydrazine thruster has several outstanding advantages such as relatively-simple structure, long/stable propellant storability, clean exhaust products, and so on. Therefore hydrazine thruster has such a wide application as orbit and attitude control system (ACS) for space vehicles. A hydrazine thruster with the medium-level thrust to be used in the ACS of space launch vehicles (SLV) has been developed, and its ground firing test result is presented in terms of thrust, impulse bit, temperature, and chamber pressure. It is verified through the performance test that the response and repeatability of thrust are very excellent, and the thrust efficiencies compared to its ideal requirement are larger than 93%.

단일액체추진제 하이드라진 추력기는 간단한 구조, 우수한 추진제 저장성, 깨끗한 반응생성물 기체 등과 같은 장점으로 수많은 우주비행체의 궤도 및 자세제어시스템으로 적용되고 있다. 우주발사체의 자세제어시스템에 적용하기 위한 중형급 하이드라진 추력기가 설계 제작되었으며, 성능검증을 위해 수행된 개발모델 추력기의 지상연소시험 결과를 추력, 임펄스 비트, 그리고 엔진 구성품별 온도 및 압력 등을 통하여 제시한다. 개발모델 엔진은 매우 우수한 추력 응답성과 재현성을 보였고, 그 추력성능 효율은 이론설계치 대비 93% 이상임을 확인할 수 있었다.

Keywords

References

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