• Title/Summary/Keyword: liquid engine development

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Development of a Simulation Program to Predict the Performance of the Multi-grade Lubricant before Blending Base Oil with Additives (기유와 첨가제 혼합 전 다등급 윤활유의 성능 예측 시뮬레이션 프로그램 개발)

  • Chun, Sang-Myung
    • Tribology and Lubricants
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    • v.28 no.2
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    • pp.47-55
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    • 2012
  • Generally, to product multi-grade oil like engine oil, a sort of mineral base oil is mixed with a fundamental additive package liquid and a polymer liquid as viscosity index improver in order to improve the lubricating property of base oil. That is, engine oil is the mixture of more than two fluids. Specially, a polymeric type liquid cannot be seen as the linear viscosity like Newtonian fluids. In this research, by using the governing equation describing non-Newtonian hydrodynamic lubrication related with the mixture of incompressible fluids based on the principle of continuum mechanics, it will be compared the bearing performance between the mixture of each liquid to be blended and multi-grade engine oil as a single fluid in a high speed hydrodynamic journal bearing. Further, it is to be found the way estimating the performance of the blended multi-grade engine lubricant in a journal bearing in advance before blending by using the physical properties of mineral base oil, fundamental additive liquid and polymer liquid of viscosity index improver. So, it can be reduced the number of trial and error to get the wanted lubricant by selecting the proper volume fraction of each liquid to satisfy the expected performance and estimating in advance the performance of various multi-grade oils before blending. Therefore, it can be shorten the developing time and saved the developing cost.

Chung-nam National University's Status of Research on Technology of the Next Generation Rocket Engine System (충남대학교 차세대 로켓엔진 시스템 기술 연구 현황)

  • Jang, Jee-Hun;Jeon, Jun-Su;Kim, Tae-Woan;Ko, Young-Sung;Kim, Sun-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2012.05a
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    • pp.196-200
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    • 2012
  • To acquire indigenous development abilities of a future space launcher, bi-propellant liquid rocket engines using environmentally clean propellants such as hydrogen peroxide and methane have been developed by Chungnam national university. The necessary development technologies for the future liquid rocket engines were defined and have been acquired step-by-step in advance by sub-scale liquid rocket engines. Core techniques of design/manufacture/experiments to develop a future prototype liquid rocket engine will be obtained by this study.

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Design of Liquid Rocket Engine System Layout (액체로켓엔진시스템 배치 안)

  • Chung Yong-Hyun;Oh Myung-Hwan;Nam Kyoung-O;Moon Jong-Hoon;Ryu Chul-Sung
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2004.10a
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    • pp.162-165
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    • 2004
  • A layout of regenerative liquid rocket engine using turbo pump has been designed for development of high performance liquid rocket engine. each components of engine system was placed by considering assembly and characteristic. first stage engine system is controled by one plane of axis gimballing and composed of four engine assembly to cluster with launch vehicle. second stage engine system is controled by two plane of axis gimballing and composed of one engine assembly. assembly and disassembly processes and required program have been developed. various shape of instruments were also developed for carrying out assembly and disassembly process efficiently

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Conceptual Design of KSLV-II 3rd Stage Engine Test Facility (한국형발사체 3단 엔진 연소시험설비 개념설계)

  • Kim, Seung-Han;Chung, Yong-Gap;Han, Yeoung-Min
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2012.05a
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    • pp.484-488
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    • 2012
  • Korea Aerospace Research Institute (KARI) performed the conceptual design of rocket engine test facility for the development and qualification of the 3rd stage liquid rocket engine for KSLV-II. The 3rd stage rocket engine test facility, which are to be constructed at Naro Space Center, will supply propellants and high-pressure gases to engine for firing test at ground and altitude conditions. The altitude test condition is obtained using a supersonic diffuser operated by the self-ejecting jet from the liquid rocket engine.

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Development of Liquid Propellant Rocket Engine for KSR-III (KSR-III 액체추진제 로켓 엔진 개발)

  • Choi Hwan-Seok;Seol Woo-Seok;Lee Soo-Yong
    • Journal of the Korean Society of Propulsion Engineers
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    • v.8 no.3
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    • pp.75-86
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    • 2004
  • KSR-III is the first Korean sounding rocket propelled by a liquid propellant propulsion system and it has been developed over 5 years using purely domestic technologies. The propulsion system of KSR-III is a 13-ton class see-level thrust liquid rocket engine(LRE) which utilizes liquid oxygen and kerosene for its propellants and employed pressurized propellant feeding and ablative cooling system. The problem of combustion instabilities which has brought the most difficulty in the development was resolved by implementation of a baffle. Through the development of KSR-III LRE, meaningful achievements have been made in the core technologies of LRE such as design of injectors and combustion chambers and test, evaluation, and control of combustion instabilities. The acquired technologies will be applied to the development of higher performance LREs necessary for future space development programs such as Korean Small Launch Vehicles(KSLV) In this paper, the development of KRE-III LRE system is described including its design, analyses. performance tests and evaluation.

Development of An Engine Modeling and an Engine Control Module for an LPG Engine (LPG 엔진 모델링 및 ECM 설계에 관한 연구)

  • 심한섭;선우명호
    • Transactions of the Korean Society of Automotive Engineers
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    • v.7 no.9
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    • pp.1-9
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    • 1999
  • Liquid Petroleum Gas (LPG) has been widely used for commercial light-duty vehicles worldwide. Since LPG has a higher octane number and a lower maximum combustion temperature than gasoline , it becomes more popular fuel for reducing exhaust emissions. In tihs study, mathematical models of air intake and fuel delivery system are presented, and a PI-controller is designed for air-fuel ratio control. Hardware and software of an engine control module (ECM) are designed for an LPG engine. The ECM is built using a Motorola MC68HC05. In order to control the air-fuel ratio at stoichiometry, the PI-control algorithm is implemented in the ECM. The experiment results show the proto LPG ECM and its control scheme perform well to meet the stoichiometric air-duel ratio requirement.

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A Case Study on Upper Stage Liquid Propellant Rocket Engine Developments (위성 발사체 상단 엔진 개발 사례 연구)

  • Nam, Chang-Ho;Lee, Eun-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.109-115
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    • 2011
  • Development cases of space launch vehicle upper stage engine were studied. HM-7, Vinci, LE-5, RL10 engines are representative upper stage engines of Europe, Japan, and United States. It was realized that upper stage engines were developed with more than two engine test facilities and the development period was 5 to 8 years accompanied with 10~11 engines.

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Application of Bellows Cryogenic Insulation for Liquid Rocket Engines (액체로켓엔진의 벨로우즈 극저온 단열재 적용)

  • Kim, YoungJun;Jung, Eunhwan
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.1057-1059
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    • 2017
  • In development of liquid-propellant rocket engine, engine gimbaling requires various types of bellows movements and cryogenic insulation is applied with movement-based design and material on each axial and circular bellows. Cryogenic insulation of Bellows for high pressure line and recirculation line are necessary to maintain cryogenic temperature for engien efficiency and protect from heat transfer and radiation of high temperature components during engine gimbaling.

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Development and Evaluation of Startup Simulation Code for an Open Cycle Liquid Rocket Engine (개방형 사이클 액체로켓엔진 시동해석 코드 개발 및 평가)

  • Jung, Taekyu
    • Journal of the Korean Society of Propulsion Engineers
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    • v.23 no.5
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    • pp.67-74
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    • 2019
  • In this paper, mathematical models of a simulation code are presented. The simulation code was developed for the startup analysis of an open cycle liquid rocket engine (LRE). Most of the components comprising an LRE, including the priming process in the propellant feeding line, were considered. A startup simulation of a 75-tonf LRE, which was used for the KSLV-II test launch vehicle (TLV), was performed. The simulation results showed good agreement with the engine acceptance test results, thus proving the validity of the startup simulation code.

A Methodology for Estimating Reliability and Development Cost of a New Liquid Rocket Engine -focused on Staged Combustion Cycle with LOX/LH2 (액체로켓엔진의 신뢰도 및 개발비용 추정 방법 -LOX/LH2 다단연소 사이클을 중심으로)

  • Kim, Kyungmee O.;Hwang, Junwoo
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.42 no.5
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    • pp.437-443
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    • 2014
  • Engine is one of the most important parts in a rocket for completing its mission successfully. In this paper, we provide a methodology for estimating reliability and development cost of a liquid rocket engine newly developed. To estimate reliability, a baseline engine is selected considering factors whose effects on reliability are unquantifiable. Then reliability of a baseline engine is adjusted to reflect the effect of factors that can be modeled quantitatively. Using the previous Transcost engine cost expressed in terms of mass and the number of hot firing tests, the engine development cost is reexpressed in reliability and thrust requirements. Finally, a numerical example is given to illustrate the application of the methodology to a turbopump rocket engine using staged combustion cycle with LOX/LH2 propellant.