• Title/Summary/Keyword: 로켓 복합 사이클

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Conceptual Design Study on Rocket Based Combined Cycle Engine (로켓 기반 복합사이클 엔진의 개념설계)

  • Kang, Sang Hun;Lee, Yang Ji;Yang, Soo Seok
    • Aerospace Engineering and Technology
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    • v.12 no.1
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    • pp.111-119
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    • 2013
  • Conceptual design of RBCC (Rocket Based Combined Cycle) engine is performed through the thermodynamic cycle analysis. The engine is designed to take off at sea level and accelerate to Mach 8 at 30 km altitude. According to the flight speed, the engine operating modes are categorized into 3 modes : Ejectorjet (~ Mach 3), Ramjet (Mach 3~6), Scramjet (Mach 6~8). As a design result, the engine has a diameter of 1 m and a length of 6.7 m. In the prediction results, its maximum thrust is 16.5 ton. In Ramjet and Scramjet modes, design condition of the engine intake influence the engine thrust according to the flight speed.

Design Study of a Dual-Mode Ramjet Engine with Large Backward-Facing Step (큰 후향 계단이 있는 이중 모드 램젯 엔진의 설계 연구)

  • Yang, Inyoung;Lee, Yang-Ji;Lee, Kyung-Jae
    • Journal of the Korean Society of Propulsion Engineers
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    • v.19 no.6
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    • pp.33-41
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    • 2015
  • Scaled model of a dual-mode ramjet engine with large backward-facing step, as a component of the rocket-based combined cycle engine, was designed. Design parameters were derived for this engine with the consideration of application for the rocket-based combined cycle engine. Design methodology was established for these design parameters. The design was partially verified through numerical study. Flow characteristics of the dual-mode ramjet engine with large backward-facing step was investigated experimentally. The design methodology for relevant design parameters established in this study was verified as feasible.

Pipe Network Analysis for Liquid Rocket Engine with Gas-generator Cycle (액체로켓엔진 가스발생기 사이클의 배관망 해석)

  • Lim, Tae-Kyu;Lee, Sang-Bok;Roh, Tae-Seong
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2012.05a
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    • pp.52-57
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    • 2012
  • A liquid rocket system consists of a combustion chamber, a gas generator, a turbo pump, and a turbine, etc. Each component is connected by supply components such as valves, pipes, and orifices. Since each component has a combined effect on engine performance, preliminary analysis for overall system must be required before the conceptual design stage. Comprehensive analysis program considered the supply system has not been developed yet. In this paper, a supply component model of the liquid rocket engine has been designed after verification of each component. The gas generator cycle with supply components has been composed. The results of the cycle has been compared to those of the F-1 engine with the representative gas generator cycle.

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Introduction to the Propulsion Systems for the Next Generation Flight Vehicles (차세대 비행체 추진기관 시스템 소개)

  • 이대성;양수석;차봉준;한영민;김춘택
    • Journal of the Korean Society of Propulsion Engineers
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    • v.4 no.3
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    • pp.74-82
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    • 2000
  • The concept and characteristics of the propulsion systems for the next generation flight vehicles are described in this paper, where Hey are grouped into air breathing engine, rocket engine and combined cycle engine according to the feeding system of oxidizer. Air breathing engine has its good reusability and superior performance at low altitude, but its usage is limited at high altitude due to the decreased air density. Rocket engine can be used over the wide range of altitude, but it has disadvantages in low specific impulse and high cost. The several types of combined cycle engine, which are being developed by the leading countries in the aerospace, are highlighted as a remarkable candidate for the next generation propulsion system.

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공기흡입형 고속추진기관 기술동향

  • Cha, Bong-Jun;Gang, Sang-Hun;Yang, Su-Seok
    • Current Industrial and Technological Trends in Aerospace
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    • v.4 no.1
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    • pp.44-54
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    • 2006
  • 초음속 또는 극초음속 비행체용 추진기관은 산화재 공급방식에 따라 공기흡입형과 로켓 그리고 이들을 혼합한 형태인 복합사이클 추진기관으로 구분할 수 있다. 그러나 재사용이 가능하다는 측면에서 미래의 추진기관들은 공기흡입형과 복합사이클 추진기관들이 주류를 이룰 것으로 예상된다. 본 논문에서는 차세대 초고속 추진기관으로 유력시 되고 있는 공기흡입형 추진기관들 중에서 램/스크램 제트 추진기관들을 중심으로 세계적인 개발동향과 기술개념을 기술하였으며 이 두 가지 추진기관들을 바탕으로 구성된 복합사이클 추진기관들에 대한 개념들을 소개하였다. 항공우주선진국들을 중심으로 차세대 고속비행체 및 고속추진기관의 실용화 개발 움직임들이 구체화 되고 있는 가운데 최근 들어 비록 미약하지만 한국항공우주연구원을 비롯한 몇 개의 기관 및 대학에서 램제트/스크램제트 추진기관에 대한 핵심 요소기술 연구들이 진행되고 있는 것은 그나마 다행이라 할 수 있으며 본 논문이 차세대 초고속 추진기관에 대한 이해를 돕는데 도움이 되기를 기대한다.

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Conceptual Design of Rocket Based Combined Cycle Engine (Rocket Based Combined Cycle Engine의 개념설계 연구)

  • Lee, Yang-Ji;Kang, Sang-Hun;Yang, Soo-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.11a
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    • pp.581-585
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    • 2009
  • In this study, conceptual design of the RBCC (Rocket Based Combined Cycle) engine was performed for the hypersonic propulsion system development. For the flight mission, RBCC engine takes off at sea level and accelerates up to Mach 8 at the altitude of 30km. By the flight speed characteristics, operating pattern of the engine is categorized into 3 modes : Ejector jet (~Mach 3), Ramjet (Mach 3~6), Scramjet (Mach 6~8). According to the engine mode characteristics, RBCC engine design and analysis was performed.

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Introduction to the Propulsion Systems for the Next Generation Flight Vehicles (차세대 비행체 추진기관 시스템 소개)

  • 이대성;양수석;차봉준;한영민;김춘택
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2000.11a
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    • pp.17-17
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    • 2000
  • 초음속 비행체 및 극음속 성층권 비행체용 추진기관으로의 사용이 검토되고 있는 차세대 추진기관들을 산화제 공급방식에 따라 공기흡입 엔진, 로켓 엔진 및 복합사이클 엔진으로 분류하여 엔진의 구성방식 및 추진특성들을 기술하였다. 공기흡입 엔진은 저고도에서의 성능이 우수하고 재사용이 가능 하지만 공기 밀도가 낮은 고 고도 영역에서의 성능이 좋지 않으며 로켓 엔진은 넓은 고도영역에서 사용이 가능한 반면 낮은 비추력 및 고비용 발사체계 등과 같은 단점들을 가지고 있다.(중략)

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Ramjet Mode Combustion Test for a Dual-Mode Ramjet Engine Model with a Large Backward-Facing Step (큰 후향 계단이 있는 이중 모드 램젯 엔진 모델의 램젯 모드 연소 시험)

  • Yang, Inyoung;Lee, Kyung-jae;Lee, Yang-ji;Kim, Chun-taek
    • Journal of the Korean Society of Propulsion Engineers
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    • v.20 no.6
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    • pp.83-90
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    • 2016
  • Ramjet mode combustion test was performed for a dual-mode ramjet engine model. The engine model consists of an air intake, a combustor and a nozzle. The combustor in the model has a large backward-facing step, designed to be used as a part of a rocket-based combined cycle engine. The test was performed at the flight speed of Mach 5 and the altitude of 24 km. Strong combustion was established only when the fuel was injected from both of the bottom-side and cowl-side wall. When the total fuel stoichiometric ratio was 1.0, distributed as 0.5 on the cowl side and 0.5 on the bottom side, the flow became subsonic at some portion in the combustor by thermal choking, i.e., ramjet mode was established for this condition.

Weight Reduction of the Reusable Launch Vehicles Using RBCC Engines (RBCC엔진을 적용한 재사용발사체의 중량저감효과)

  • Kang, Sang Hun;Lee, Soo Yong
    • Journal of the Korean Society of Propulsion Engineers
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    • v.17 no.3
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    • pp.56-66
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    • 2013
  • Weight reduction of the VTHL / TSTO type of the reusable launch vehicles using RBCC engines are investigated. To predict weight and thrust of the vehicles, equations of motion are analyzed. Analysis results are compared with specifications of existing launch vehicles for validations. For the mission of inserting 2.5 ton payload to 200 km circular orbit, the case A, which uses the RBCC engine in the 1st stage shows smaller weight than the case B, which uses the RBCC engine in the 2nd stage. The weight of the case A shows only 25.8% of a existing rocket launch vehicle's weight.

Multi-Ejector Design for High Altitude Simulation (고고도 환경 모사를 위한 멀티 이젝터 설계)

  • NamKoung, Hyuck-Joon;Shim, Chang-Yol;Lee, Jae-Ho;Park, Sun-Sang
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.705-708
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    • 2011
  • Ejector system can induce the secondary flow or affect the secondary chamber pressure by both shear stress and pressure drop which are generated in the primary jet boundary. Ejectors are widely used in a range of applications such as a turbine-based combined-cycle propulsion system and a high altitude test facility for rocket engine, pressure recovery system, desalination plant and ejector ramjet etc. The primary interest of this study is to set up an design procedure on the configuration and operating condition of multi-ejector for the various high altitude simulation.

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