• Title/Summary/Keyword: 액체로켓부스터

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Performance Analysis of KSLV-II Launch Vehicle with Liquid Rocket Boosters (액체로켓 부스터를 부착한 한국형발사체의 발사 성능 분석)

  • Yang, Won-Seok;Choi, Jeong-Yeol
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.42 no.7
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    • pp.544-551
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    • 2014
  • A program of launch vehicle performance analysis is composed for the education of the conceptual design of launch vehicles and the requirement analysis for the propulsion system design. The program is applied for the mission analysis of space launch vehicles based on KSLV-II with liquid rocket boosters. The 75-ton class liquid rocket engine is assumed for the boosters by referring the mass ratio of KSLV-II second stage. The launch performance analysis is carried out for KSLV-II with 2, 3 and 4 boosters by targeting the circular orbit of 700 km altitude. The trajectory is assumed as two-dimension considering the variation of the flight environment. Payload of advanced KSLV-II could be increased to maximum 3 tons, though it is limited by the thrust performance of the upper stage.

Perspective of Technology for Liquid Rocket Engines (액체로켓엔진 기술 전망)

  • Cho, Won Kook;Ha, Sung Up;Moon, Insang;Jung, Eun Whan;Kim, Jin Han
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.44 no.8
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    • pp.675-685
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    • 2016
  • A research area on liquid rocket engine has been suggested. Downsizing through combustion pressure rise and low price are major issues to gas generator cycle engines. A very high pressure turbopump and material against oxidizer rich environment may be necessary technologies for staged combustion cycle engines. Integrated analysis saving computing time is the trend of rocket engine systems analysis area. Other important research topics are the methane engine for reusable booster to reduce the cost, 3D printing and materials for high temperature or oxidizer rich environment.

Development Trends of Liquid Methane Rocket Engine and Implications (액체로켓 메탄엔진 개발동향 및 시사점)

  • Lim, Byoungjik;Kim, Cheulwoong;Lee, Keum-Oh;Lee, Keejoo;Park, Jaesung;Ahn, Kyubok;Namkoung, Hyuck-Joon;Yoon, Youngbin
    • Journal of the Korean Society of Propulsion Engineers
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    • v.25 no.2
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    • pp.119-143
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    • 2021
  • Selecting liquid methane as fuel is a prevailing trend for recent rocket engine developments around the world, triggered by its affordability, reusability, storability for deep space exploration, and prospect for in-situ resource utilization. Given years of time required for acquiring a new rocket engine, a national-level R&D program to develop a methane engine is highly desirable at the earliest opportunity in order to catch up with this worldwide trend towards reusing launch vehicles for competitiveness and mission flexibility. In light of the monumental cost associated with development, fabrication, and testing of a booster stage engine, it is strategically a prudent choice to start with a low-thrust engine and build up space application cases.

Technical Review and Analysis of Ramjet/Scramjet Technology I. Ramjet Engine (Liquid Ramjet, Ducted Rocket) (램제트/스크램제트의 기술동향과 소요기술 분석 I. 램제트 엔진(액체램제트, 덕티드로켓))

  • Sung Hong-Gye;Yoon Hyun-Gull
    • Journal of the Korean Society of Propulsion Engineers
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    • v.10 no.1
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    • pp.72-86
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    • 2006
  • A technical review of current ramjet propulsion is presented. In addition to summarize the current status of ramjet technology, new key techniques like Boosting technique easily adapting total impulse of booster, flame stabilization technique with minimized ramjet combuster length, variable nozzle-inner-surface technique realizing wide flight-envelop, and thermal protection technique for long operating time are identified. Actually various Ramjet propulsion technology has been matured and expanding to both military and combined cycle application. Yet many opportunities remain to be challenged by future generations of explorers to utilize s typical ramjet propulsion system for multi-purpose(multi-platform and multi-target) missiles, for example, American JSSCM and Russian Yakhont missiles, improving both reliability of techniques and downsizing development cost of new propulsion system.

Review of the Solid Propulsion Trend in the Launch Vehicle(1) (발사체 고체 추진기관 동향 리뷰(1))

  • Lee, Tae-Ho
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2012.05a
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    • pp.201-212
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    • 2012
  • In general solid propulsion offers cost effective, large thrust capabilities comparing to the liquid propulsion which offers high specific impulse and restart capabilities. Therefore solid propulsion is well fitted for the first stage and boosters. BBL approach has been studied for the launch vehicle because of cost effectiveness, limited development time and low risk. Using of the carbon fiber epoxy resin in the solid rocket motor case is expanded, and specially high strength fibers are more attracted since its inert mass reduction.

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A Study on the Calculation of Minimum Safety Distance during Storage and Combustion Test of Solid Propellants for Launch Vehicles (발사체 고체추진제의 저장 및 시험 시 안전거리 산정에 관한 연구)

  • Shin, Ahn-Tae;Park, Byung-Mun;Byun, Hun-Soo
    • Korean Chemical Engineering Research
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    • v.59 no.2
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    • pp.180-185
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    • 2021
  • In accordance with the revision of the US-Korea missile guidelines, restrictions on the use of solid propellants for space launch vehicles have been completely lifted. The solid propellant can be used as a solid propellant rocket like the KSR-1 (Korea Sounding Rocket-1), and can also be used as a thrust augmentation booster for liquid fuel launch vehicles. It is known that solid propellants have a lower risk of explosion than liquid propellants. but if an accident such as an explosion at the Alcantara Launch Center in Brazil occurs, it can lead to a large-scale personal accident. In order to prevent such large-scale accidents, it is necessary to review and reflect the minimum safety distance during use, storage and combustion test of solid propellants from the planning phase of the project. In this paper, the minimum safety distance for safe use of the solid propellant is presented by dividing it into storage facilities and combustion tests.

Review of the Solid Propulsion Trend in the Launch Vehicle(1) (발사체 고체 추진기관 동향 리뷰(1))

  • Lee, Tae-Ho
    • Journal of the Korean Society of Propulsion Engineers
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    • v.16 no.5
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    • pp.97-107
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    • 2012
  • In general, solid propulsion offers cost effective, large thrust capabilities comparing to the liquid propulsion which offers high specific impulse and restart capabilities. Therefore, solid propulsion is well fitted for the first stage and boosters. Building Block Launcher(BBL) approach has been studied for the launch vehicle because of cost effectiveness, limited development time and low risk. Using of the carbon fiber epoxy resin in the solid rocket motor case is expanded, and specially high strength fibers are more attracted since its inert mass reduction.

Preliminary Study of Gas Generator After Burning Cycle Engine for Upper Stages (상단용 가스발생기 후연소 싸이클 엔진 기초연구)

  • Moon, In-Sang;Shin, Ji-Chul
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.05a
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    • pp.159-162
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    • 2008
  • In this study, various cycles of liquid rocket engines were surveyed and specifically gas generator after burning cycle was investigated for upper stage motors. The engines for the upper stage can be categorized into three group based on the cycles and propellants at the diagram. Kerosene engines which adapt the gas generator after burning cycle and are located in the region II, are characterized for high combustion pressure and complexity. This cycle usually needs more than two pumps to use the turbine power efficiently. The fuel line can be divided into the gas generator line and the combustor line, and only the gas generator line is need to be pressured more because the combustion pressure in the gas generator is much higher than that of the combustor. Basically, all the oxidizer goes into the gas generator and than to the combustor, thus the auxiliary LOx pump is not critically necessary. However, for the various reasons, the LOx line requires a booster pump. A gas generator after burning cycle engines produces relatively high specific impuls than that of the open cycle engines. Thus it is suitable for upper stages of launch vehicles.

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