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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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Journal of the Korean Society of Propulsion Engineers
Journal Basic Information
Journal DOI :
The Korean Society of Propulsion Engineers
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Volume & Issues
Volume 14, Issue 6 - Dec 2010
Volume 14, Issue 5 - Oct 2010
Volume 14, Issue 4 - Aug 2010
Volume 14, Issue 3 - Jun 2010
Volume 14, Issue 2 - Apr 2010
Volume 14, Issue 1 - Feb 2010
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LES of Breakup and Atomization Characteristics of a Liquid Jet into Cross Turbulent Flow
Yang, Seung-Joon ; Koo, Ja-Ye ; Sung, Hong-Gye ; Yang, Vigor ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 2, 2010, Pages 1~9
LES(Large eddy simulation) of breakup and droplet atomization of a liquid jet into cross turbulent flow was performed. Two phase flow of gas and liquid phases were modeled by the mixed numerical scheme of both Eulerian and Lagrangian methods for gas and liquid droplet respectively. The breakup process of a liquid column and droplets was observed by implementing the blob-KH wave breakup model. The penetration depth into cross flow was comparable with experimental data for several variants of the liquid-gas momentum flux ratio by varying liquid injection velocity. SMD(Sauter Mean Diameter) distribution downstream of jet was analyzed.
Improvements of Model Scramjet Engine Performance and Ground Test
Kang, Sang-Hun ; Lee, Yang-Ji ; Yang, Soo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 2, 2010, Pages 10~18
Scramjet engine is one of the core parts of hypersonic vehicle of next generation and being investigated by many countries. Korea Aerospace Research Institute performed a ground test of the model scramjet engine S1 in 2007. And, S2 model which is improved from S1 model in engine startability and thrust was tested with HIEST (High Enthalpy Shock Tunnel) at Kakuda Space Center of JAXA. Design condition of S2 model was Mach 6.7, however, it was tested at Mach 7.7 as an off-design condition test. As a test result, flow separation was found at the inside of the intake, but the engine showed stable combustion pressure distribution. Furthermore, compared to other test models, S2 model showed a good performance value in thrust and specific impulse.
Study on Phase-Amplitude Characteristics in a Simplex Swirl Injector with Low Frequency Range
Khil, Tae-Ock ; Chung, Yun-Jae ; Yoon, Young-Bin ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 2, 2010, Pages 19~28
Generally, combustion instability is generated by the mutual coupling between the heat release and the acoustic pressure in the combustor. On the occasion, the acoustic pressure generates the oscillation of the mass flow rate of propellant injected from injector, and this oscillation again affects combustion in the combustor. So, the dynamic characteristics of the injector have been studied to control combustion instability using injector itself in Russia from 1970's. In order to study injector dynamics, a mechanical pulsator for forced pressure pulsation is produced and the method to quantify the mass flow rate of the propellant that is oscillating at the exit of the injector is developed. With the pulsator and the method, pulsating values of the mass flow rate, pressure, liquid film thickness, and axial velocity generated at the exit of the simplex swirl injector are measured in real time. And phase-amplitude characteristics of each parameter are analyzed using these pulsating values acquired at the exit of the simplex swirl injector.
A Study on the Combustion Characteristics of Paraffin wax/LDPE Blended fuel
Kim, Soo-Jong ; Cho, Jung-Tae ; Lee, Jung-Pyo ; Moon, Hee-Jang ; Sung, Hong-Gye ; Kim, Jin-Kon ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 2, 2010, Pages 29~38
The experimental study on paraffin wax/LDPE blended fuel for hybrid rocket was performed. Various combustion characteristics of blended fuel were compared with pure paraffin, HTPB, HDPE and SP-1a fuel in order to evaluate the performance of blended fuel. The regression rate of lab-scale and large-scale motor using pure paraffin fuel was increased by 10.2 and 9.8 factor when respectively compared to that of HDPE. The regression rate factor of blended fuel was 3.4 in which the regression rate of blended fuel was higher than that of HTPB and HDPE, but lower than that of pure paraffin, SP-1a fuel. The values of characteristic velocity and specific impulse of blended fuel was higher than those of pure paraffin, HTPB and HDPE, and almost the same as SP-1a fuel. As these results, it was confirmed that blended fuel can be an effective solid fuel for hybrid rocket.
Generation of Displacement Signal for Realizing Road Profile using the Accelerometer
Kim, Jong-Tye ; Kim, Cheol-Woo ; Kim, Taek-Hyun ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 2, 2010, Pages 39~45
In the recent years, it is important to evaluate the durability and the reliability of the vehicle, aircraft, and structure. Especially, in case of the vehicle, the durability and reliability are tested by driving test after making prototype vehicles. However, these methods require many costs and efforts for the experiment are needed to react the defects of product. This problems can be settled by simulator which supplies the realistic environments. In this parer, four-axial road simulator with hydraulic power and driving program to operate are made up. The displacement road profile is realized by accelerometers. For the verification the real-vehicle experiment is executed and road profile obtained from the experiment is verified by four-axial road simulator.
A Study on Combustion Characteristic with the Variation of Oxidizer phase in Hybrid Rocket Motor using PE/
Lee, Jung-Pyo ; Kim, Gi-Hun ; Kim, Soo-Jong ; Kim, Hak-Chul ; Moon, Hee-Jang ; Sung, Hong-Gye ; Kim, Jin-Kon ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 2, 2010, Pages 46~53
The purpose of this paper is to study combustion characteristics with the different phase of oxidizer in hybrid rocket combustion. HDPE(High Density Polyethylene) as fuel and
) as oxidizer were used to perform the experiments. An investigation was performed for a change of the regression rate, pressure of combustion chamber and combustion efficiency according to the variation of oxidizer phase. In case of using
as oxidizer, the regression rate is not significantly different from using
as oxidizer. It is considered that combustion energy is much larger than latent heat energy which was used in the evaporation of liquid oxidizer. However propulsion performance efficiency for
showed lower value than for
. By increasing the flow rate of liquid oxidizer, heat transfer needed for vaporization of liquid oxidizer was increased, which resulted in the growth of combustion instability.
Development of High Fidelity Supersonic Flow Air Data Processing Algorithm
Choi, Jong-Ho ; Yoon, Hyun-Gull ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 2, 2010, Pages 54~62
This paper describes the development of high fidelity air data processing algorithm which can be applied into an air data system for a high speed aerial vehicle. Unlike the previous air data system, current algorithm used several pre-determined pressure data which were obtained with computational fluid dynamic approach without using total pressures having enough sensor redundancy and fault detection ability. The verification of current algorithm was done by commercial software Matlab and Simulink.
A Study of Construction of a Hydrogen Peroxide Supply System for Liquid Rocket Engine
Jeon, Jun-Su ; Lee, Yang-Suk ; Kim, Young-Mun ; Choi, Yu-Ri ; Ko, Young-Sung ; Kim, Yoo ; Kim, Sun-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 2, 2010, Pages 63~70
A construction process of hydrogen peroxide supply system was investigated to use hydrogen peroxide as an oxidizer of bi-propellant liquid rocket engine. To use hydrogen peroxide as a rocket propellant, it has to be in high concentration over 90%. It is very important to make the supply system free of pollutants, because highly concentrated hydrogen peroxide has a characteristic of hypersensitive reaction to pollutants such as dust and oil sludge. We suggested the cleaning and passivation process of main components to minimize pollutants of the supply system. In conclusion, we verified stability of the constructed supply system by leak test and hot test.
A Technical Review of Endothermic Fuel Use on High Speed Flight Cooling
Kim, Joong-Yeon ; Park, Sun-Hee ; Chun, Byung-Hee ; Kim, Sung-Hyun ; Jeong, Byung-Hun ; Han, Jeong-Sik ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 2, 2010, Pages 71~79
As hypersonic flight speeds and engines efficiencies increase, heat loads on an aircraft and it's engine increase. Because the temperature of the air flow is too high to cool the aircraft structure at hypersonic flight speeds, it is essential to use the aircraft fuel as the primary coolant. Endothermic fuels are liquid hydrocarbon aircraft fuels which are able to absorb the heat loads by undergoing endothermic reactions, such as thermal and catalytic cracking. The endothermic reactions are improved by catalysts which change the extent of reaction and product distribution. At high temperature, liquid hydrocarbons would lead to coke formation that can reduce the effectiveness of heat exchanger and cause rapid degradation of the catalyst, thus endothermic capacity of endothermic fuels is limited to the temperature at which coke doesn't form. In this study, the essential cooling technologies by applying endothermic fuels and the properties of the endothermic fuels are described.