• Title/Summary/Keyword: Liquid Propulsion

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Concept Design of the Propulsion System Test Complex for Heavy Liquid Rocket (대형 액체로켓 추진기관 시스템 시험설비 개념설계)

  • Kim, Ji-Hoon;Yoo, Byung-Il;Cho, Nam-Kyung;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.789-792
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    • 2011
  • Before doing the flight test, the ground test for liquid rocket propulsion system is helpful for improving its reliability and reducing the development money. Therefore, by constructing the Propulsion System Test Complex for heavy liquid rocket propulsion system development, we expect that it will be the first step for making the commercial launcher which will be competitive in the international launch service market.

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A Generalized Method applied to the Analysis on the Longitudinal Instability of Liquid Propulsion System (액체 추진기관 시스템 축방향불안정성 해석을 위한 동특성 모델링 일반화 기법)

  • Lee, Han-Ju;Kim, Ji-Hoon;Jung, Dong-Hoon;Oh, Seung-Hyub
    • 한국전산유체공학회:학술대회논문집
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    • 2008.03b
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    • pp.424-427
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    • 2008
  • The longitudinal instability (POGO) of the rocket should not be occurred during the whole flight time for the large class liquid propulsion system to complete a mission successfully. The longitudinal instability is caused by the resonance between the propulsion system and rocket structure in the low frequency range below 50Hz, ordinarily. We can consider various types of propulsion system in the early stage of rocket development. So the longitudinal instability analysis tool is needed for corresponding to each propulsion system. This article deals the generalized method applied to the analysis on the low frequency dynamic characteristics of various types of liquid propulsion system.

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Development of the Remote Control System for Liquid Rocket Propulsion System (액체로켓 추진개관 원격제어시스템 개발)

  • 이주열;김재문;김영수;홍일희
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2003.05a
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    • pp.207-210
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    • 2003
  • The purpose of this work is to introduce the Remote Control System for KSR-III Liquid Rocket Propulsion System. We developed the high reliable Fire control System that needed for long distance control. We carried out a real time remote control and measuring for KSR-III lust Liquid Propulsion Rocket in Korea using TCP/IP Ethernet network method and Fiber-optic communication method. Also HMI operation program developed guarantee confidential control, monitoring and analysis for Fire control operation.

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AN ANALYTICAL STUDY ON THE DYNAMIC CHARACTERISTICS OF A LIQUID PROPULSION SYSTEM

  • Lee Han Ju;Lim Seok Hee;Jung Dong Ho;Kim Yong Wook;Oh Seung Hyub
    • Bulletin of the Korean Space Science Society
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    • 2004.10b
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    • pp.325-327
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    • 2004
  • The longitudinal instability (POGO) of the rocket should not be occurred during the whole flight time for the large class liquid propulsion system to complete a mission successfully. The longitudinal instability is caused by the resonance between the propulsion system and rocket structure in the low frequency range below 50Hz, ordinarily. Analysis on the low frequency dynamic characteristics on the liquid propulsion system with staged combustion cycle engine system was performed as a preliminary study on the longitudinal instability analysis.

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Design Process of Liquid-Propellant Propulsion System for Space Launch Vehicle (우주발사체용 액체추진시스템 설계 프로세스)

  • Kim Hui-Tae;Han Sang-Yeop;Lee Han-Ju;Cho Kie-Joo;Oh Seung-Hyub
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • v.y2005m4
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    • pp.147-150
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    • 2005
  • Space launch vehicles mainly use the liquid-propellant propulsion system which has easy thrust control ability and high specific impulse for that the payload like satellite and spacecraft should be entered into exact orbit. However, the liquid-propellant propulsion system is very difficult to develop because it is more complicate than the solid rocket propulsion system and demands very high technology. In space launch vehicle developing procedure the system design level is very important thing to reduce cost, shorten schedule, and improve the performance. The system design process was introduced for selecting the best liquid-propellant propulsion system on this paper.

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Computer Codes for MDO: Application to the Evaluation of the Interest of a New Propulsion Concept for an Upper Stage of Future Launchers

  • Calabro, Max
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.03a
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    • pp.543-545
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    • 2008
  • The Inner Arch developed several softwares: $\circ$ One dedicated to solid propulsion project : APSOL $\circ$ One dedicated to liquid propulsion projects ELIS A third one, PERFOL, is used to optimize the trajectory and the propulsion parameters The paper will describe the main software used for this study and illustrate the interest of these tools to make the first design of a new version of a launch vehicle with optimisation both of intrinsic propulsion parameters and of the trajectory.

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Development of C/SiC Composite Parts for Rocket Propulsion (로켓 추진기관용 C/SiC 내열부품 개발)

  • Kim, Yunchul;Seo, Sangkyu
    • Journal of the Korean Society of Propulsion Engineers
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    • v.23 no.2
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    • pp.68-77
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    • 2019
  • C/SiC composites were developed by a liquid silicon infiltration(LSI) method for use as heat-resistant parts of solid and liquid rocket propulsion engines. The heat resistance characteristics according to the composition ratio (carbon / silicon / silicon carbide) were evaluated by specimen test through arc plasma, supersonic torch test. An ablation equation for oxidation reactions was presented. Through the combustion test it was verified that various parts such as nozzle insert, exit cone and combustion chamber heat resistant parts for rocket propulsion can be manufactured and proved high ablation performance and thermal structure performance.

The Performance Evaluation of C/SiC Composite for Rocket Propulsion Systems (추진기관용 C/SiC 복합재료의 특성 평가)

  • Kim, Yun-Chul
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.11a
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    • pp.433-438
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    • 2009
  • The main objective of this research effort is to develop the performance of C/SiC composites manufactured by LSI (Liquid Silicon Infiltration) method for solid and liquid rocket propulsion system and ensure the performance analysis technique. The high performance and reliability of C/SiC composite are proved for solid and liquid rocket propulsion system. And the performance analysis technique related to mathematical ablation model is originated.

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A Review on Major Foreign Research Trend of Monomethylhydrazine Reaction for Space Propulsion Part I : Thermal Decomposition Reaction of Monomethylhydrazine (우주추진용 모노메틸하이드라진 반응에 대한 주요 해외연구 동향 조사 Part I : 모노메틸하이드라진의 열분해 반응)

  • Jang, Yohan;Lee, Kyun Ho
    • Journal of Aerospace System Engineering
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    • v.10 no.1
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    • pp.66-73
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    • 2016
  • Space propulsion system produces required thrust for satellites and space launch vehicles by using chemical reactions of a liquid fuel and a liquid oxidizer typically. For example, monomethylhydrazine-dinitrogen tetroxide, liquid hydrogen-liquid oxygen and RP-1-liquid oxygen are conventional combinations of liquid propellants used for the liquid propulsion system. Among several liquid propellants, the monomethylhydrazine is expecially preferred for a satellite fuel due to its better storability in liquid phase during a relatively long mission period under a space environment. Thus, a development importance of a bipropellant system using the monomethylhydrazine fuel is recognized recently as the national space program proceeds on a large scale. The objective of the present study is to review a foreign research trend of a thermal decomposition reaction of monomethyhydrazine to understand a fundamental basis of its chemical reaction to prepare for domestic development in future.

Development of Underwater Rocket Propulsion System for High-speed Cruises (고속 주행을 위한 수중용 로켓추진기관 개발)

  • Kwon, Minchan;Yoo, Youngjoon;Heo, Junyoung;Hwang, Heeseong
    • Journal of the Korean Society of Propulsion Engineers
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    • v.23 no.3
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    • pp.112-118
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    • 2019
  • The development of an underwater rocket propulsion system was described in this paper. Throttle able liquid propellant and hybrid rocket propulsion systems were selected for underwater propulsion. A subscale liquid rocket combustion chamber and it's portable stand were developed and their applicability was examined. 1.5-ton.f and 1.8-ton.f hybrid rockets were developed for underwater applications. The test results indicated that the 18-ton.f hybrid rocket fully complies to the performance and underwater cruise stability requirements; thus, its development was concluded to be successfully complete.