• Title/Summary/Keyword: Bi-propellant Thruster

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Development and Verification Test of a Bi-propellant Thruster Using Hydrogen Peroxide and Kerosene

  • Yu, I Sang;Kim, Tae Woan;Ko, Young Sung;Jeon, Jun Su;Kim, Sun Jin
    • International Journal of Aeronautical and Space Sciences
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    • v.18 no.2
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    • pp.270-278
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    • 2017
  • This paper describes development procedure and verification test results of a bi-propellant thruster using hydrogen peroxide and kerosene. The design thrust of the thruster is about 500 N and six swirl type coaxial injectors were used. The passage type manifolds were employed for the injector head to reduce the response time. The passage was designed to minimize stagnation points and recirculation region to ensure uniform flow distribution and sufficient cooling performance through flow analysis using Fluent. A catalytic igniter using hydrogen peroxide was installed at the center of the injector head. The propellant feeding and spray characteristics were confirmed by hydraulic tests. Combustion tests were performed on design and off-design points to analyze combustion characteristics under various mixture ratio conditions. The combustion test results show that combustion efficiency was over 95 % and chamber pressure fluctuation were less than 1.5 % under all test conditions.

A study of thrust modeling of bi-propellant rocket engine (이원 추진제 로켓 엔진의 추력 모델링 연구)

  • Jeong,Hae-Seung;Kim,Yu;Ham,Mi-Suk;Park,Eung-Sik
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.31 no.8
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    • pp.85-90
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    • 2003
  • To control spacecraft including satellite, we should understand precisely the performance of propulsion system and the program logic with appropriate format for satellite operations. In this study, the thruster performance functions was generated by using the best curve fitting for performance data from bi-propellant thrusters. Detailed thruster performance data are, in general, company proprietary information, therefore real firing tests were performed to understand the basic characteristics of the performance curve. Experimental rocket motor utilize liquid oxygen and kerosine as propellant and designed average thrust was 100 pound.

Performance Evaluation of Hydrogen Peroxide with Storage Conditions (온도 조건에 따른 과산화수소의 저장성평가)

  • Chung, Seung-Mi;An, Sung-Yong;Kwon, Se-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.11a
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    • pp.105-108
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    • 2008
  • Nowadays, as there is so much interest in environment, hydrogen peroxide attracts attention as an eco-propellant. Hydrogen peroxide is widely used for mono-propellant of thruster, and oxidizer of bi-propellant rocket. Especially, it is used as mono-propellant of the thruster for attitude control of satellite and military weapons. So, the need of long time storage of hydrogen peroxide appears and storage test is required. In this paper, necessity of storage test of hydrogen peroxide and some conditions and methods are introduced. In addition, the results of storage tests under some condition are compared and analyzed.

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Study for Design and Performance Characteristics of Small Bipropellant Thruster using $H_2O_2$/Kerosene (과산화수소/케로신 소형 이원추진제 추력기의 설계 및 성능특성에 관한 연구)

  • Kim, Jung-Hoon;Lee, Jae-Won;Jeon, Young-Jin;Chae, Byoung-Chan;Jeon, Jun-Su;Kim, Yoo;Kim, Sun-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.05a
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    • pp.41-45
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    • 2009
  • The small-sized bi-propellant thruster using a high concentrated hydrogen peroxide and kerosene as the oxidizer and fuel was designed and fabricated in this study. The water cold-flow test was performed to verify the performance characteristics of the injector. The mixing head assembly used in this model thruster was designed as a structure to combine igniter, injectors and film cooling, which are capable of regulating each mass flowrate. This maximize the experimental verification and efficiency of the design optimization. Finally, the mass flowrate and spray pattern of injector were evaluated by the hydraulic test. Therefore, the design validity of the mixing head was verified.

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Effect of Internal Flow Guide in Pintle Tip on Pintle Injector Thruster Combustion (핀틀 인젝터의 팁 내부 유동 가이드가 연소 성능에 미치는 영향)

  • Lee, Keonwoong;Nam, Jeonsoo;Radhakrishnan, Kanmaniraja;Koo, Jaye
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.48 no.9
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    • pp.703-709
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    • 2020
  • Pintle injector is known to have been adopted as injector of Lunar Module Descent Engine (LMDE) and contributed to success of the Apollo program and recently used in merlin engine. In this study, 500N Lab-Scale pintle injector thruster was manufactured and the combustion experiment with LOx/GCH4 was conducted. However, the proto-type thruster was showed some problems, such as low combustion efficiency and melting of pintle tip. To solve these problems, the flow guide in pintle tip was suggested through the CFD simulation. After addition of flow guide module, the combustion efficiency increased and pintle tip did not melt until the end of combustion.