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- W830485006 abstract "ABSTRACT A system design has been conducted of the liquid rocket engine for Korean launch vehicle (KSLV-II, Korea Space Launch Vehicle II). The present turbopump-fed liqui d rocket engine of vacuum thrust 76 ton and vacuum specific impulse 297 sec adopts gas generator cy cle. The combustion pressure of the regeneratively cooled combustor is 60 bar. The propellant is LO x/kerosene. The engine is started by pyrostarter and the combustor is ignited by TEA (TriEthylAlumin ium). The engine system performance and the subsystems performance requirements are given through e nergy balance analysis. The combustion pressure, specific impulse and the engine mass are a nalyzed to be reasonable comparing with the published data. The startup analysis method which will be used in the future has been validated against the turbopump-gas generator coupled test. The tuning method for performance variation of the engine which is not actively controled has bee n prepared by mode analysis and performance deviation analysis.초 록 한국형 발사체 (KSLV-II, Korea Space Launch Vehicle II)에 적용될 액체로켓엔진의 시스템 설계를 수행하였다. 진공 추력 76톤, 진공 비추력 297 sec인 본 엔진은 가스발생기 사이클로 터보펌프 가압방식을 적용한다. 연소기는 재생냉각형이며 연소압 60 bar이다. 추진제는 액체산소/케로신 조합이다. 엔진 시동은 파이로시동기를 이용하며 연소기 점화는 TEA (TriEthylAluminium)를 사용한다. 에너지 밸런스 해석을 통해서 엔진 시스템 성능과 서브시스템 요구 성능을 결정하였다. 연소압, 비추력 및 엔진 무게의 적정성을 사례분석을 통하여 평가하였다. 터보펌프-가스발생기 연계시험과 비교하여 시동 해석 방법을 검증함으로써 향후 적용을 위한 준비를 마쳤다. 본 엔진은 능동제어를 적용하지 않으며 모드해석과 분산해석을 통해서 성능 보정 방안을 확정하였다.Key Words: Liquid Rocket Engine(액체로켓엔진), System Design(시스템 설계), Regenerative Cooling(재생냉각), Gas Generator Cycle(가스발생기 사이클), LOx/kerosene(액체산소/케로신)" @default.
- W830485006 created "2016-06-24" @default.
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- W830485006 date "2010-01-01" @default.
- W830485006 modified "2023-09-23" @default.
- W830485006 title "Liquid Rocket Engine System of Korean Launch Vehicle" @default.
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