• Title/Summary/Keyword: 촉매점화

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Study on 1,200 N-class bipropellant rocket engine using decomposed $H_2O_2$ and kerosene (분해된 과산화수소와 케로신을 이용한 1,200 N 급 이원추진제 로켓 엔진의 연구)

  • Jo, Sung-Kwon;An, Sung-Yong;Kim, Jong-Hak;Yoon, Ho-Sung;Kwon, Se-Jin
    • Journal of the Korean Society of Propulsion Engineers
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    • v.14 no.6
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    • pp.69-78
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    • 2010
  • As part of preliminary study for development of 1,200 N-class bipropellant rocket engine with the concentrated hydrogen peroxide, bipropellant engine elements were designed and experimentally tested. The catalysts of $MnO_2$ and $MnO_2$ added Pb as an additive were compared to achieve high decomposition performance and the catalytic reactor with $MnO_2$ added Pb was designed and its decomposition efficiency of 97.2% was achieved. The autoignition tests of kerosene by decomposed hydrogen peroxide were carried out under various equivalence ratios to ignite without additional ignition sources. Autoignition were achieved in all experimental conditions and $C^*$ efficiencies at each condition were at or above 90%. From the measured thrust results, the highest value was 830 N which is in corresponds with 1,035 N at vacuum level assuming $C^*$ efficiency equals $I_{sp}$ efficiency.

Study on 1,200 N-class bipropellant rocket engine using decomposed $H_2O_2$ and kerosene (분해된 과산화수소와 케로신을 이용한 1,200 N 급 이원추진제 로켓 엔진의 연구)

  • Jo, Sung-Kwon;An, Sung-Yong;Kim, Jong-Hak;Yoon, Ho-Sung;Kwon, Se-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2010.05a
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    • pp.156-164
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    • 2010
  • As part of preliminary study for development of 1,200 N-class bipropellant rocket engine with the concentrated hydrogen peroxide, bipropellant engine elements were designed and experimentally tested. The catalysts of $MnO_2$ and $MnO_2$ added Pb as an addictive were compared to achieve high decomposition performance and the catalytic reactor with $MnO_2$ added Pb was designed and its decomposition efficiency of 97.2% was achieved. The autoignition tests of kerosene by decomposed hydrogen peroxide were carried out under various equivalence ratios to ignite without additional ignition sources. Autoignition were achieved in all experimental conditions and $C^*$ efficiencies at each condition were at or above 90%. From the measured thrust results, the highest value was 830 N which is in corresponds with 1,035 N at vacuum level using 94.1% theoretical $I_{sp}$.

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Ignition Characteristics According to Mixture ratio of Catalyst Ignitor using Green Propellant (친환경 추진제 점화기 설계 및 혼합비에 따른 점화 특성)

  • Chae, Byoung-Chan;Lee, Yang-Suk;Ko, Young-Sung;Kim, Yoo;Kim, Sun-Jin;Jeon, Young-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.11a
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    • pp.111-114
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    • 2009
  • A catalyst ignitor of small thrust engine using hydrogen peroxide and kerosene was designed and fabricated, which confirmed mass flow rate for design pressure through the water cold-flow test in this study. In order to investigate ignition performance, it was changed that mixture ratio for kerosene mass flow rate in a position which heat of hydrogen peroxide decomposition comes to a steady state. And we confirmed stable ignition property in a wide range of mixture ratio.

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Thermal Phenomena of an N2O Catalyst Bed for Hybrid Rockets Using a Porous Medium Approach (다공성 매질 접근법을 적용한 하이브리드 로켓 N2O 촉매 점화기의 열적 현상)

  • 유우준;김수종;김진곤;장석필
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.34 no.9
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    • pp.89-96
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    • 2006
  • In this study, fluid flow and thermal characteristics in a catalyst bed for nitrous oxide catalytic decomposition which is introduced as a hybrid rocket ignition system for small satellites were theoretically considered. To analyze the thermal phenomena of the catalyst bed, a so-called porous medium approach has been opted for modeling the honeycomb geometry of the catalyst bed. Using a Brinkman-extended Darcy model for fluid flow and the one-equation model for heat transfer, the analytical solutions for both velocity and temperature distributions in the catalyst bed are obtained and compared with experimental data to validate the porous medium approach. Based on the analytical solutions, parameters of engineering importance are identified to be the porosity of the catalyst bed, effective volumetric ratio, the ratio of the radius of the catalyst bed to the radius of a pore, heat flux generated by a heater, and pumping power. Their effects on thermal phenomena of the catalyst bed are studied.

HMC 엔진의 전자제어 시스템 소개

  • 장익순;이재곤
    • Journal of the KSME
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    • v.32 no.10
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    • pp.876-882
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    • 1992
  • 여기에서는 삼원촉매 장착엔진을 정밀하게 제어(연료 제어, 공회전 제어, 점화시기 제어, Purge Air 제어 등)하여 삼원촉매의 효율을 향상시키고, 그 결과 배기가스를 감소시킴과 더불어 운전성 및 동력성능을 향상시킨 엔진 전자 제어 시스템의 개요를 간단히 소개하였다. 앞으로도 북미지 역의 배기가스 관련법규가 더욱 강화될 것으로 예상되며, 이에 대응한 엔진 제어 시스템에 대한 지속적인 연구 개발이 필요하리라 생각된다.

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An investigation of autoignition characteristics of kerosene by decomposed hydrogen peroxide (분해된 과산화수소를 이용한 케로신의 자연점화특성 조사)

  • Jo, Sung-Kwon;Kwon, Se-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.11a
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    • pp.397-400
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    • 2008
  • Traditional propellants which have a hypergolic characteristic have a high performance but also have disadvantages of toxicity and complex handling requirement. In order to replace these propellants, one of the alternatives is hydrogen peroxide which generates high temperature oxygen and water vapor after catalytic reaction. In this paper, autoignition characteristics of kerosene by decomposed hydrogen peroxide were investigated to perform fundamental research for designing a thruster using hydrogen peroxide and kerosene propellants. Contraction ratio, whether flame holder exists or not, and feeding pressure of propellants were selected as variables. From the experiments for different mixture ratio, we confirmed the ignition stability is strongly affected by a feeding pressure of propellants.

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Ignition and Extinction Characteristics of a Low Thrust Combustion Chamber using Green Propellant according to Sequence of the Combustion Test (친환경 추진제를 사용하는 저추력 액체로켓엔진의 연소시험 시퀀스에 따른 점화 및 소염 특성)

  • Kim, Young-Mun;Jeon, Jun-Su;Choi, Yu-Ri;Ko, Young-Sung;Kim, Yoo;Kim, Sun-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.11a
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    • pp.130-133
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    • 2009
  • The sequence of the propellant supply is very important for the reliable and safe operation of a LRE combustion test. So combustion performance tests were performed to find an optimum test sequence by changing supply time of propellants and purge gas in the moment of ignition and extinction. The liquid rocket engine consisted of a catalytic ignitor and six swirl-coaxial injectors which used hydrogen peroxide and kerosene. Conclusively, an optimum sequence was found for stable combustion in the moment of ignition and extinction.

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Heterogeneous Ignition of $H_2/O_2/CO_2$ Mixture Over Platinum Catalyst (수소/산소/이산화탄소 혼합기의 백금촉매반응특성 : 비균일 반응의 점화 온도)

  • Nam, Chang-Ho;Shin, Hyun-Dong
    • 한국연소학회:학술대회논문집
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    • 2001.11a
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    • pp.90-96
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    • 2001
  • Catalytic ignition of $H_2/O_2/CO_2$ mixtures over platinum catalyst is experimentally investigated by using microcalorimetry. For comparison, $N_2$ and Ar is also used as diluent gas. The gas mixture flows toward platinum foil heated by electric current at atmosphere pressure and ambient temperature. The ignition temperature range 350-445K according to the fuel ratio, dilution ratio and diluent gas. It increases as the fuel ratio and dilution ratio increase. $H_2/O_2$ mixture with $CO_2$ ignites at higher temperature than with other diluents by 30-50K. Several experimental evidences show the inhibition effects of $CO_2$ in $H_2-O_2$ heterogeneous reaction is considerable

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A study on the combustion performance with Hydrogen Peroxide / Kerosene (과산화수소/ 케로신을 추진제로 한 200N급 엔진의 연소 성능에 관한 연구)

  • Kim, Young-Mun;Hwang, Oh-Sik;Lee, Yang-Suk;Ko, Young-Sung;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.61-64
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    • 2009
  • A study on the variation of combustion performance by oxidizer/fuel ratio was conducted. Shower head type injector was used. Injector propelled by liquid kerosene and liquid hydrogen peroxide. The designed operation condition for thrust and combustion pressure were 200N and 10bar. It is found that optimum oxidizer/fuel ratio.

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A Study of Catalyst Temperature Rise Effect by using UEGI(Unburned Exhaust Gas Ignition) Technology during Cold-Start (냉시동시 미연 배기가스 점화 기술을 이용한 촉매 온도 상승 효과에 관한 연구)

  • Kim, C.S.;Chun, J.Y.;Choi, J.W.;Kim, I.T.;Ohm, I.Y.;Cho, Y.S.
    • Proceedings of the KSME Conference
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    • 2000.11b
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    • pp.335-340
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    • 2000
  • Most vehicle's exhaust emissions come from the cold transient period of the FTP-75 test. In this study, UEGI technology was developed to help close-coupled catalytic converter (CCC) reach light-off temperature within a few seconds after cold-start. In the UEGI system, unburned exhaust mixture is ignited by four glow plugs installed upstream of the catalyst. Experimental results showed that the temperature of CCC rises faster with the UEGI technology, and the CCC reaches light-off temperature earlier. Under the conditions tested, the light-off time of the baseline case was 62 seconds and that of the UEGI case was 33 seconds.

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