• Title/Summary/Keyword: liquid engine development

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Development of Liquid Rocket Engine Test Facility (한국형발사체 엔진 지상 연소시험설비 개발)

  • 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.479-483
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    • 2012
  • This paper describes the development status of rocket engine test facility for the performance evaluation of liquid rocket engine of KSLV-II 1st stage. Design specification and composition of rocket engine test facility are suggested based on the design requirements. The results of the basic design of rocket engine test facility will be used as base data for the detail design and construction of rocket engine ground test facility of KSLV-II 75tonf liquid rocket engine.

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A Correction Method for Operating Mode Analysis of Gas Generator Cycle Liquid Propellant Rocket Engine (가스발생기 사이클 액체로켓엔진작동 모드 해석의 보정 방법)

  • Nam, Chang-Ho;Moon, Yoonwan;Park, Soon Young;Chung, Enhwan
    • Journal of the Korean Society of Propulsion Engineers
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    • v.22 no.6
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    • pp.104-110
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    • 2018
  • Operating mode analysis of a liquid propellant rocket engine(LRE) is a crucial tool through the development of an engine. The operating mode analysis of an engine based on a collection of the acceptance tests of components shows discrepancies when compared to the test results. We propose a correction method for performance parameters to develop an engine analysis model for the gas generator cycle of an LRE. In order to simulate engine behavior, the performance parameters for the analysis model are tuned based on the test results of the 75tf engine of KSLV-II.

Liquid Hydrogen/Liquid Oxygen Rocket Engine Technology (액체수소/액체산소 로켓엔진 기술 검토)

  • Cho, Nam-Kyung;Park, Soon-Young;Kim, Seong-Han;Han, Yeong-Min
    • Journal of the Korean Society of Propulsion Engineers
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    • v.26 no.2
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    • pp.47-59
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    • 2022
  • Liquid hydrogen/liquid oxygen rocket engines with highest specific impulse have been developed since the 1950s and used until now to maximize the capability of space launch vehicles. Domestic liquid hydrogen infrastructures for the production, transportation and distribution are being expanded at world-class level with the rise of hydrogen economy, which is a great opportunity for the performance enhancement for indigenous space launch vehicles. In this paper, feasibility of applying liquid hydrogen as a propellant is investigated in various aspects. The status of domestic liquid hydrogen infrastructure, the technologies required for liquid hydrogen engines, and operational aspects for safe handling of hydrogen are reviewed. In addition, test facilities for developing hydrogen engines are introduced briefly.

A Study on the Development Process of the Liquid Rocket Engine for the Upper Stage of the Korea Space Launch Vehicle-II (한국형발사체 상단 액체로켓엔진의 개발과정에 대한 고찰)

  • Seo, Kyoun-Su;Park, Soon-Young;Nam, Chang-Ho;Moon, Yoonwan
    • Journal of the Korean Society of Propulsion Engineers
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    • v.26 no.1
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    • pp.68-76
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    • 2022
  • Upper stage of the Korea Space Launch Vehicle-II(KSLV-II) uses a 7-tons class liquid rocket engine and is an open gas generator cycle with a turbopump supply method that uses kerosene/liquid oxygen as the propellant combination. This study first provided a brief overview of the design and development process of the upper stage engine. In addition, it introduced the solutions and results applied to some of the problems that occurred during the development process of the upper stage engine.

Research and Development Status of Combustion Chamber of Liquid Rocket Engine for KSLV-II (한국형발사체 액체로켓엔진 연소기 연구 개발 현황)

  • Han, Yeoung-Min;Lee, Kwang-Jin;Kim, Jong-Gyu
    • 한국연소학회:학술대회논문집
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    • 2012.11a
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    • pp.291-294
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    • 2012
  • The research and development status of combustion chamber of liquid rocjet engine for Korea Space Launch Vehicle(KSLV-II) are briefly described. The cold and hot firing tests of uni-element injector, the performance/heat flux measurement/hot firing tests of subscale combustion chamber and the performance/stability rating/regenerative cooling/hot fire tests of 30ton-class combustion chamber were successfully performed. Based on these results, the research and development of combustion chamber for 75ton-class liquid rocket engine are underway.

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Verification Test of KSR-III Liquid Propellant Rocket Prototype Engine (KSR-III 액체추진로켓 시제엔진 검증시험)

  • 하성업;류철성;설우석
    • Journal of the Korean Society of Propulsion Engineers
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    • v.5 no.4
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    • pp.67-74
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    • 2001
  • Based on the national space development project, the necessity of developing liquid propellant rocket engine is revealed to secure the basic technology for the development of individual artificial-satellite launcher. Consequently, KARI (Korea Aerospace Research Institute) is developing a liquid propellant rocket engine for the KSR-III. Currently, a prototype engine using kerosene/LOx which produces 13-ton thrust is designed, fabricated and tested. In this paper, test procedure and technique for liquid propellant rocket engine are introduced with the analysis of static and dynamic test data.

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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.

Study on the Emergency Protection System of Liquid Rocket Engine (액체로켓엔진 비상보호시스템 연구)

  • Kim, Seung-Han;Han, Yeoung-Min
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.97-103
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    • 2011
  • This paper describes the main considerations for the development of engine emergency protection system and applications to preliminary engine development tests. Emergency protection system performed its role without failure to shutdown test very quickly for the prevention of development of malfunctioning of test articles, which protected test articles and test facility in all abnormal situation occurred during preliminary engine development test program. This results will be used for the development of engine emergency protection system.

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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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Making-Decision Method on Major Issues of Liquid Rocket Engine Development using Analytic Hierarchy Process (계층분석방법을 이용한 액체로켓엔진 개발의 주요 이슈에 대한 의사결정 방안)

  • Seo, Kyoun Su;Jeong, Eun Hwan
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.1104-1107
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    • 2017
  • In this paper, we focused on Analytic Hierarchy Process(AHP) as an efficient means of decision-making on the major issues that may arise during the liquid rocket engine development, reviewed the validity and applicability of the AHP through the problem of selecting the propellant of the liquid rocket engine.

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