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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
Selecting the target year
Dynamic Characteristics for Fuel Shutoff Valve of a Gas Generator
Lee, Joong-Youp ; Huh, Hwan-Il ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 4, 2010, Pages 1~9
Fuel shutoff valve of a gas generator controls propellant mass flowrate of a rocket engine, by using pilot pressure and spring force. The developing fuel shutoff valve can be self sustained even though pilot pressure is removed in an actuator. Therefore, it is necessary to analyze the characteristics of the forces with respect to the opening and closing of the valve in order to evaluate its performance. In light of this, the valve has been designed to adjust the control pressure for the opening of the poppet and to determine the working fluid pressure at which the valve starts to close. This paper also has been designed dynamic model using the AMESim and predicted flow coefficient of the valve by Fluent CFD analysis. Various results from the prediction and the analysis have been compared with experiments. Finally, dynamic characteristics of the valve have been verified with experimental results.
Experimental Study on a Two-Stage Light-Gas Gun
Lee, Jung-Keun ; Kim, Heuy-Dong ; Koo, Ja-Ye ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 4, 2010, Pages 10~15
Light gas guns have a large number of applications in various fields of engineering. A two-stage light-gas gun can produce an extremely high pressure in a very short interval of time. In general, the two-stage light-gas gun is made up of a high pressure tube, a compression tube and a launch tube, each stage being separated by diaphragms. This can be employed efficiently in the application of ultra-high pressure liquid jets. In the present study, experiments are carried out to investigate the projectile velocity and pressure behavior in the tubes according to the pressure changes at the frist diaphragm opening. In the present study result was found that the rupture pressure of the first diaphragm has a dominant influence on piston acceleration.
Studies on Through-Bulkhead Initiation Module using VISAR
Jang, Seung-Gyo ; Baek, Sung-Hyun ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 4, 2010, Pages 16~24
A Through-Bulkhead Initiation Module(TBIM) works as the shock-wave generated by the detonation of donor explosive transmits to acceptor explosive. In order to estimate the minimum thickness of the bulkhead of TBIM, the structural stress of TBIM housing is calculated via modeling analysis, and which shows a sufficient margin in strength as the minimum thickness is bigger than 0.1 mm. The free surface velocity at the metal to explosive interface is measured using VISAR to determine the optimal thickness of bulkhead. The shock pressure is calculated from the measured free surface velocity, and the probability of TBIM with respect to the thickness of bulkhead is estimated by comparing the sensitivity of acceptor explosive with it.
Hexane Vapor Concentration Measurement of a Liquid Jet in Crossflow
Oh, Jeong-Seog ; Lee, Won-Nam ; Lee, Jong-Geun ; Santavicca, Dominique A. ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 4, 2010, Pages 25~31
The vapor concentration of hexane in a liquid spray jet in crossflow was qualitatively measured on the basis of the infrared (IR) extinction techniques. The objectives of the present study are to understand the whole evaporation process from droplet breakup to vapor and to confirm the usefulness of IR emission method in a lab-scale ramjet combustor. From the experimental results, we concluded that hexane vapor mole fraction increased with temperature rise and kept nearly constant during the variation of fuel to air momentum ratio.
Rib-Dimple Compound Cooling Techniques in a Gas Turbine Blade Cooling Channels with an Aspect ratio (4:1)
Choi, Yong-Duck ; Kim, Seok-Beom ; Lee, Yong-Jin ; Kim, Jin-Kon ; Kwak, Jae-Su ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 4, 2010, Pages 32~38
Heat transfer coefficients in a dimpled channel, a ribbed channel, and a rip-dimple compound channel were measured by the transient liquid crystal technique. The channel aspect ratio, the rib height, the rip pitch, and the rib angle were 4:1, 6 mm, 60 mm and
, respectively. The dimple diameter and the center-to-center distance were 6mm and 7.2 mm, respectively, and the Reynolds number range was 30,000-50,000. Results showed that the heat transfer coefficients were increased by the angled rib. For the dimple-rib compound cooling cases, the heat transfer coefficients were further augmented and the thermal performance factor for the case was the highest.
A Study on the Residual Stress Evaluation of Autofrettaged SCM440 High Strength Steel
Kim, Jae-Hoon ; Shim, Woo-Sung ; Yoon, Young-Kwen ; Lee, Young-Shin ; Cha, Ki-Up ; Hong, Suck-Kyun ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 4, 2010, Pages 39~45
Thick-walled cylinders, such as a cannon or nuclear reactor, are autofrettaged to induce advantageous residual stresses into pressure vessels and to increase operating pressure and the fatigue lifetimes. As the autofrettage level increases, the magnitude of compressive residual stress at the bore also increases. The purpose of the present paper is to predict the accurate residual stress of SCM440 high strength steel using the Kendall model which was adopted by ASME Code. Hydraulic pressure process was applied in the inner part and thick-walled cylinders were autofrettaged up to 30% overstrain levels. Electro polishing on the surface of autofrettage specimen was performed to get more accurate residual stress. Residual stresses were measured by X-ray diffraction method. The autofrettage surface which was plastically deformed analyzed using a scanning electron microscope(SEM). Although there were some differences in measured residual stress and numerical results, it has a tendency to agree comparatively with each other.
Research Trend and Histories of Rocket Engines using Hydrogen Peroxide and Liquid Methane as Green Propellants
Kim, Sun-Jin ; Lee, Yang-Suk ; Ko, Young-Sung ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 4, 2010, Pages 46~58
Hydrogen peroxide(HP) and liquid methane have deserved renewed considerations as green propellants in recent years, because main design concerns in the development of the new generation propulsion system for spacecrafts are concentrated on low operation cost and environmental cleanness. Although HP has a long history of application to aerospace propulsion systems due to high density, mono-propellant characteristics and low toxicity, it had been replaced by hydrazine and liquid oxygen due to extreme performance requirement during the cold war. But HP has received a renewed interest due to its increased stability and many researches have been conducted to develop high performance LREs(Liquid Rocket Engines) using HP. Liquid methane has also received a new interest in rocket propulsion system for the future space exploration according to its possibility of ISRU(In-Situ Resource Utilization).
Measurement Uncertainty Assessment of Altitude Performance Test for a Turboshaft Engine
Yang, In-Young ; Lee, Bo-Hwa ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 4, 2010, Pages 59~64
Measurement uncertainty assessment was performed for altitude performance test for a turboshaft engine. Mathematical models of measurement were suggested for major performance parameters such as shaft horse power, fuel flow, specific fuel consumption, and airflow. The procedure was compared with the test of turbojet or turbofan engines. Uncertainty involved with the test condition measurement was assessed. Influence of the test condition measurement uncertainty on the corrected performance data was discussed. Uncertainty assessment result was provided for a example test case using a real altitude test facility. For major performance parameters, measurement uncertainties were assessed as 0.65~1.09% including the test condition measurement uncertainty, 0.36~0.94% not including it.
Performance Analysis of an Electric Powered Small Unmanned Aerial Vehicle
Lee, Chang-Ho ; Kim, Sung-Yug ; Kim, Dong-Min ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 4, 2010, Pages 65~70
A small unmanned aerial vehicle(UAV), which uses a propulsion system consisting of electric motor and battery, weighs less than 8 kg, capable of hand launch. Because it is easy to operate and able to transmit image information in real time, the use of small UAV has been increasing. However, very few analysis methods or analysis results on flight performance of the small UAV have been known so far. In this paper, the performance analysis methods of a small UAV, which is manufactured to study an electric powered UAV, are suggested and their results are achieved. Aerodynamic data of the vehicle are obtained by making use of gliding performance from actual flight test, and required thrust and required power by flight speed are predicted. In addition, the methods to predict range and endurance in case of using battery as power source are suggested and their results are achieved.
Analytic Considerations of Liquid Rocket Engine Thrust Chamber Design for the KSLV-II
Choi, Hwan-Seok ; Han, Yeoung-Min ; Ryu, Chul-Sung ; Kim, Seong-Ku ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 4, 2010, Pages 71~80
The KSLV-II(Korea Space Launch Vehicle-II) which being a successor of the KSLV-I is a space launch vehicle capable of delivering 1.5 ton-class satellite into a low earth orbit. The development of a 75 tonf-class liquid rocket engine(LRE) is planned on the basis of the technologies mastered through the preceded research of a 30 tonf-class LRE. The thrust chamber of the LRE is required to have higher combustion stability, structural integrity and thermal durability. This paper deals with the design requirements of the 75-tonf thrust chamber and a variety of technical considerations which have been conducted analytically in the course of the design for the realization of the requirements.