The design and performance on 200N-class bipropellant rocket engine using decomposed H2O2 and Kerosene
Mono-propellant thrusters are widely utilized in satellites and space launchers. In many cases, they are using hydrazine as a propellant. However, hydrazine has high toxicity and high risks in using for launch campaign. Recently, low-toxic (green) propellant is being highlighted as a replacement for...
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National Institute for Aerospace Research “Elie Carafoli” - INCAS
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Online Access: | http://bulletin.incas.ro/files/lee_jang__vol_11_iss_3.pdf |
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doaj-6ea5225b937e4e5dbf44a2ccad81ca1f2020-11-25T02:07:16ZengNational Institute for Aerospace Research “Elie Carafoli” - INCASINCAS Bulletin2066-82012247-45282019-09-011139911010.13111/2066-8201.2019.11.3.9The design and performance on 200N-class bipropellant rocket engine using decomposed H2O2 and KeroseneYang-Suk LEE0Jun Hwan JANG1Koreaaero Industry, Sacheon-si, Gyeongsangnam-do, Korea icueyes@nate.comMechanical Design Major Department of Mechanical Engineering, Yuhan University, Gyeonggi-do, Korea bulbearj@gmail.coMono-propellant thrusters are widely utilized in satellites and space launchers. In many cases, they are using hydrazine as a propellant. However, hydrazine has high toxicity and high risks in using for launch campaign. Recently, low-toxic (green) propellant is being highlighted as a replacement for hydrazine. In this paper, 200N bi-propellant engine using hydrogen peroxide/kerosene was designed/manufactured, and the spray or atomization characteristic and inflation pressure were determined by cold flow test, and combustion and pulse tests in a single cycle same as previous methods were conducted. As uniformly supplying hydrogen peroxide through plate-type orifice to a catalyst bed, the hot gas was created as a reaction with hydrogen and catalyst. And then, it was confirmed that the ignition is possible on the wide range of O/F ratio without additional ignition source. The liquid rocket engine with bi-propellant of hydrogen peroxide/kerosene and design/test methods which developed in this study are expected to be utilized as an essential database for designing of the ignitor/injector of bi-propellant liquid rocket engine using hydrogen peroxide/kerosene with high-thrust/performance in near future.http://bulletin.incas.ro/files/lee_jang__vol_11_iss_3.pdfGreen PropellantHydrogen PeroxideRCS(Reaction Control System)Space Launcher |
collection |
DOAJ |
language |
English |
format |
Article |
sources |
DOAJ |
author |
Yang-Suk LEE Jun Hwan JANG |
spellingShingle |
Yang-Suk LEE Jun Hwan JANG The design and performance on 200N-class bipropellant rocket engine using decomposed H2O2 and Kerosene INCAS Bulletin Green Propellant Hydrogen Peroxide RCS(Reaction Control System) Space Launcher |
author_facet |
Yang-Suk LEE Jun Hwan JANG |
author_sort |
Yang-Suk LEE |
title |
The design and performance on 200N-class bipropellant rocket engine using decomposed H2O2 and Kerosene |
title_short |
The design and performance on 200N-class bipropellant rocket engine using decomposed H2O2 and Kerosene |
title_full |
The design and performance on 200N-class bipropellant rocket engine using decomposed H2O2 and Kerosene |
title_fullStr |
The design and performance on 200N-class bipropellant rocket engine using decomposed H2O2 and Kerosene |
title_full_unstemmed |
The design and performance on 200N-class bipropellant rocket engine using decomposed H2O2 and Kerosene |
title_sort |
design and performance on 200n-class bipropellant rocket engine using decomposed h2o2 and kerosene |
publisher |
National Institute for Aerospace Research “Elie Carafoli” - INCAS |
series |
INCAS Bulletin |
issn |
2066-8201 2247-4528 |
publishDate |
2019-09-01 |
description |
Mono-propellant thrusters are widely utilized in satellites and space launchers. In many cases, they are using hydrazine as a propellant. However, hydrazine has high toxicity and high risks in using for launch campaign. Recently, low-toxic (green) propellant is being highlighted as a replacement for hydrazine. In this paper, 200N bi-propellant engine using hydrogen peroxide/kerosene was designed/manufactured, and the spray or atomization characteristic and inflation pressure were determined by cold flow test, and combustion and pulse tests in a single cycle same as previous methods were conducted. As uniformly supplying hydrogen peroxide through plate-type orifice to a catalyst bed, the hot gas was created as a reaction with hydrogen and catalyst. And then, it was confirmed that the ignition is possible on the wide range of O/F ratio without additional ignition source. The liquid rocket engine with bi-propellant of hydrogen peroxide/kerosene and design/test methods which developed in this study are expected to be utilized as an essential database for designing of the ignitor/injector of bi-propellant liquid rocket engine using hydrogen peroxide/kerosene with high-thrust/performance in near future. |
topic |
Green Propellant Hydrogen Peroxide RCS(Reaction Control System) Space Launcher |
url |
http://bulletin.incas.ro/files/lee_jang__vol_11_iss_3.pdf |
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