• Title/Summary/Keyword: Liquid Rocket

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Test Facility Improvement for Hot Firing Test of a 7-tonf Combustor in Sub-scale model (7톤급 연소기 축소형 모델 시험을 위한 설비 개량)

  • Kang, Dong-Hyuk;Lim, Byoung-Jik;Kim, Hyeon-Jun;Choi, Hwan-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2012.05a
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    • pp.498-501
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    • 2012
  • The Model Rocket Engine Test Facility has been improved to develop the Korea Space Launch Vehicle II(KSLV-II). The modified Model Rocket Engine Test Facility will be used to develop 7-tonf class liquid rocket engine combustor. The test result and test technique acquired from this facility will be used to develop the high performance liquid rocket engine combustor. This paper describes the modified Model Rocket Engine Test Facility for a Sub-scale model test of the 7-tonf class combustor.

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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 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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Development of Thrust Measurement System and Study of Calibration in Liquid Rocket Engine (액체 로켓 엔진에서의 추력 측정 장치 개발과 calibration에 관한 연구)

  • Park, Soo-Hwan;Park, Hee-Ho;Kim, Yoo;Cho, Nam-Choon;Keum, Young-Tag
    • Journal of the Korean Society of Propulsion Engineers
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    • v.6 no.1
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    • pp.39-46
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    • 2002
  • It is very difficult to measure an exact thrust in liquid rocket engine compared to solid rocket motor, however it is very important to estimate a performance of engine for developing rockets. To get a good result, we have to concern about errors of measurement and find a method of calibration. In this research, we developed new thrust measurement system for liquid rocket engine.

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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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.

Flow Characteristics of Cryogenic Oxidizer in Liquid Propellant Rocket Engine (액체로켓 엔진에서의 극저온 산화제의 유동 특성)

  • 조남경;정용갑;문일윤;한영민;이수용;정상권
    • Journal of the Korean Society of Propulsion Engineers
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    • v.6 no.4
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    • pp.15-23
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    • 2002
  • In most cryogenic liquid rocket engines, liquid oxygen manifold and injector are not thermally insulated from room temperature environment fur reducing system complexity and the weight. This feature of cryogenic liquid rocket engine results in the situation that cryogenic liquid oxygen flow is easy to be vaporized especially in the vicinity of the manifold and the injector wall. The research in this paper is focused on two-phase flow phenomena of liquid oxygen in rocket engine. Vapor fraction was estimated by comparing the measured two-phase flow pressure drop in engine manifold and the injector with ideal single phase pressure drop. Heat flux into cryogenic flow is estimated by measuring the wall temperature on the engine manifold to examine boiling characteristics. Suitable correlations for cryogenic two-phase flow were also reviewed to see their applicability. In addition, the effect of vapor generation in liquid rocket engine manifold and injector on engine performance and stability was considered.

Numerical Study of CH4/LOx Combustion of Shear-coaxial Injector in High Pressure Combustion Chamber of Liquid Rocket (액체로켓 동축인젝터(CH4/LOx)의 고압 연소실 내 연소 유동장에 대한 수치적 연구)

  • Kim, Jung Eun;Jeung, In-Seuck
    • 한국연소학회:학술대회논문집
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    • 2014.11a
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    • pp.311-313
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    • 2014
  • High pressure combustion with multiphase--liquid, gas, and supercritical phase--mixtures are widely used technology in the high efficiency liquid propellent rocket engine. This is the typical characteristics differentiate from the combustor of conventional air-breathing engines. Therefore, successful research of high pressure combustion at supercritical condition is essential to develope a high efficiency liquid rocket engine. Numerical studies have been carried out to explore capabilities of numerical method for LOx-CH4 non-premixed flames at high pressure. In this paper, corresponding numerical results are presented and compared with experimental result of MASCOTTE facility.

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A Study on Cooling Characteristics of Combustion Gas by Liquid Nitrogen in a Liquid Rocket Engine (액체질소를 이용한 액체 로켓 엔진 연소 가스 냉각 특성 연구)

  • Jeon, Jun-Su;Lee, Yang-Suk;Song, Jae-Kang;Kim, Yoo;Ko, Young-Sung
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2007.11a
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    • pp.147-150
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    • 2007
  • In this study, cooling characteristics of combustion gas were investigated by injecting liquid nitrogen into liquid rocket combustion chamber. A injection ring of liquid nitrogen was installed between a combustion chamber and a mixing chamber which was designed for mixing of combustion gas and nitrogen. At first, a ignition test of liquid rocket engine was conducted to verify a stable combustion process and 10 second combustion tests were successfully conducted. The results showed that combustion gas of LRE could be cooled by using liquid nitrogen.

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Research about the cooling of a small size rocket nozzle (소형로켓 노즐의 냉각에 관한 연구)

  • Go, Tae-Sig;Shim, Jin-Ho
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2007.04a
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    • pp.365-369
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    • 2007
  • The solid rocket interacts circumscriptively in terms of is many more than liquid rocket. It is uncontrollable than liquid rocket because all part of combustion is decided such as Mixture ratio of propellant, burning time and area. However, production cost is cheap and because authoritativeness security can be easy and enlarge the early speed that follow thrust-to-weight ratio, it is used comprehensively by small size rocket. Considered about nozzle cooling to control phenomenon that burn by thermal conduction in interior wall of nozzle that follow in thrust increase of solid rocket and erosion phenomenon by combustion gas of high speed.

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