• Title/Summary/Keyword: Rocket engine

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Transient Analysis of Liquid Rocket Engine around the Nominal Thrust Level (정상상태 부근에서의 액체로켓 엔진의 과도해석)

  • Choi Hwan-Seok;Seol Woo-Seok;Park Soon-Young
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2004.10a
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    • pp.68-76
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    • 2004
  • It is essential to develop a transient engine system analysis model for turbopump fed type liquid rocket engine development, especially for deriving engine system test number and conditions. In this study, we proposed a mathematical model of turbopump fed type liquid rocket engine, and inspected transient mode changes around the nominal thrust level of a rocket engine according to variations of trust control valve's opening ratio. To verify the results, we solved the same problem with AnaSyn software from Russia, and concluded that the transient code showed the similar results within $2\%$ with AnaSyn.

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Research of a Methodology for a Liquid Rocket Engine Development (액체로켓엔진 개발을 위한 위기관리 방법론 연구)

  • Moon, In-Sang;Jeong, Yong-Hyun;Kim, Cheul-Woong
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2006.11a
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    • pp.211-215
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    • 2006
  • It is a known fact that much effort, time and cost are needed to develop a new launch vehicle. Among the many components consisting of the launch vehicle, a rocket engine is a one of the most important and difficult part to develop in which many risks may lie dormant because very active chemical reaction occurs inside the engine while the engine is also required optimum ratio of the mass and performance. This research focused on the risk mitigation to develop the rocket engine using the example of recently developed US rocket engine.

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Estimation Methods for Turbine Nozzle Throat Area Reduction of A LOx/Kerosene Gas Generator Cycle Liquid Propellant Rocket Engine (액체산소/케로신 가스발생기 사이클 액체로켓엔진 터빈 노즐목 면적 변화 추정 방법)

  • Nam, Chang-Ho;Moon, Yoonwan;Park, Soon Young;Kim, Jinhan
    • Journal of the Korean Society of Propulsion Engineers
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    • v.23 no.5
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    • pp.101-106
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    • 2019
  • Carbon deposition on the turbine nozzle throat of a LOx/kerosene gas generator cycle(open cycle) engine causes performance reduction of the engine. Estimation methods for a turbine nozzle throat area are proposed. The discharge coefficient of the turbine nozzle was estimated with the turbine gas properties such as gas constant, specific heat ratio, and temperatures. The pressure ratio and temperature ratio of the turbine nozzle throat, was utilized to estimate the discharge coefficient also. Estimated discharge coefficient of turbine nozzle throat of KSLV-II 1st stage engine shows the carbon deposition effects on the turbine nozzle throat of a LOx/kerosene open cycle engine.

A Literature Survey and Application of System Analysis of the Liquid Rocket Engine (액체로켓엔진 시스템 해석 문헌 고찰 및 응용)

  • Cho, Won-Kook;Park, Soon-Young
    • 한국전산유체공학회:학술대회논문집
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    • 2008.03b
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    • pp.328-331
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    • 2008
  • A literature survey has been reported of the systems analysis on the liquid rocket engines. The analysis tools are mainly about the calculation of the rocket engine performance at the early days. However recent trend shows that researchers try to develop an integrated environment of distributed analysis tools for faster and cheaper analysis. This article presents the systems analysis results of the liquid rocket engine of gas generator cycle using the published mass estimating model. The specific impulse change for various thrust to weight ratio agrees qualitatively well with the published data.

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Cool Down Characteristics of 7 Tonf-class Liquid Rocket Engine for KSLV-II (한국형발사체 7톤급 액체로켓엔진 냉각 특성)

  • Im, Ji-Hyuk;Yu, Byungil;Lee, Kwang-Jin;Han, Yeoung-Min
    • Journal of the Korean Society of Propulsion Engineers
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    • v.25 no.1
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    • pp.50-57
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    • 2021
  • Engine cool down process is necessary for the liquid rocket engines using cryogenic propellants in order to meet the requirement of engine inlet temperature. This paper evaluates the cool down characteristics of oxidizer supply pipeline and engine in prechill process prior to the engine firing tests, and calculate the quantity of liquid oxygen consumption.

Design of Mixing Head Part of Combustion Chamber for 8tonf Class Staged Combustion Cycle Rocket Engine (8톤급 다단연소 사이클 로켓엔진 연소기 혼합헤드 설계)

  • Kim, Dongki;Ha, Seong up;Moon, Il yoon;Moon, Insang
    • Journal of Aerospace System Engineering
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    • v.9 no.2
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    • pp.34-40
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    • 2015
  • Staged combustion cycle engines are well known to have high combustion efficiencies and specific impulse. In this study, design of mixing head part of combustion chamber for 8tonf class staged combustion cycle rocket engine (ES-08) was performed. Structural stability of the mixing head part of the combustion chamber is very important design factor because it is loaded by high temperature and high pressure of fuel and oxidizer as well as by thrust load simultaneously. Uniformity of flow distributions of the propellants to the injectors is also important factor. First, a basic configuration for the ES-08 mixing head part was designed on the basis of the structural design requirements. And then, the structural analyses were performed on the basic configuration as well as some of reinforced configurations. As the structural analyses results, the most stable configuration was selected for the ES-08 mixing head part. In order to examine the uniformity of the flow distributions of the propellants through the manifold of the mixing head, flow analysis was performed based on the selected configuration. The results of the flow analysis showed that the fuel and the oxidizer were uniformly supplied to the injector.

Energy Balance Analysis of 30 t Thrust Level Liquid Rocket Engine (추력 30톤급 액체로켓엔진의 에너지 밸런스 해석)

  • Cho, Won-Kook;Park, Soon-Young;Kim, Chul-Woong
    • Transactions of the Korean Society of Mechanical Engineers B
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    • v.36 no.5
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    • pp.563-569
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    • 2012
  • An energy balance analysis is conducted for a 30 t thrust level liquid rocket engine. The relations between thrust and combustion pressure, between thrust and propellant flow rate, and between combustion pressure and fuel pump pressure rise are compared against those indicated by a published database of the existing rocket engines. A combustion pressure higher than the old design value is obtained, implying that the present design is high-performance oriented. The thrust to propellant flow rate ratio is the same as that of the existing engines, indicating that the specific impulse performance is at the usual level. The fuel pump pressure rise is found to be slightly high when the combustion pressure is considered, and it is attributed to the pressure budget of the present ground test engine not being optimized.

A System Analysis of the Turbopump Type Liquid Rocket Engine (터보펌프식 액체로켓엔진의 시스템 해석)

  • Lee, Jin-Kun;Kim, Jin-Han
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.32 no.5
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    • pp.109-115
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    • 2004
  • A 1-D system design program has been developed for the preliminary design of the turbopump system in liquid rocket engines, which use LOx and kerosene as propellants. Gasgenerator cycle and staged combustion cycle were considered as turbopump type liquid rocket engine systems. In the system analysis, mass flow balance, thrust, specific impulse, mixture ratios, turbopump power, and turbine expansion ratio of engine system were analyzed. Results show that most of the parameters agree well with real engine parameters except gasgenerator. Therefore, the l-D system design program developed in this study can be used to derive the preliminary design parameters of a turbopump with any thrust level liquid rocket engine.

Program Development for the Mode Calculation of Gas-Generator Cycle Liquid Rocket Engine (가스발생기 사이클 액체로켓 엔진의 모드 해석 프로그램 개발)

  • Park, Soon-Young;Cho, Won-Kook
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.11a
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    • pp.366-370
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    • 2008
  • Mode analysis is very important for the development of liquid rocket engine in various applications. We developed a mode analysis program for the gas-generator cycle liquid rocket engine by proposing 13 independent equations with 13 independent variables which can be solved by Newton method. As an example we calculated the change of engine operating mode according to the control valve's loss coefficient change located in the gas-generator oxidizer supply line. And we concluded that this program can give basic idea for the mode analysis of gas-generator cycle liquid rocket engine.

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Methodology of Liquid Rocket Engine Diagnosis (액체로켓엔진의 진단 방법론 연구)

  • Kim, Cheul-Woong;Park, Soon-Young;Cho, Won-Kook
    • Aerospace Engineering and Technology
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    • v.11 no.2
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    • pp.182-194
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    • 2012
  • To develop a liquid rocket engine with high reliability and safety under constraints of limited time and budget an optimal diagnosis system for the engine needs to be developed in parallel with the development of the engine. This paper is intended to set a development direction of the diagnosis system for the liquid rocket engine through the literature survey and addresses possible engine defects, characteristics of parameters for diagnosis and diagnostic methods including real-time diagnosis, post-test/post-flight diagnosis, fault detection method, parameter circuit method and test diagnosis. In addition tasks to be performed in the design and operation phases of the engine and foreign application case of engine diagnosis are presented.