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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
> Journal Vol & Issue
Journal of the Korean Society of Propulsion Engineers
Journal Basic Information
Journal DOI :
The Korean Society of Propulsion Engineers
Editor in Chief :
Volume & Issues
Volume 16, Issue 6 - Dec 2012
Volume 16, Issue 5 - Oct 2012
Volume 16, Issue 4 - Aug 2012
Volume 16, Issue 3 - Jun 2012
Volume 16, Issue 2 - Apr 2012
Volume 16, Issue 1 - Feb 2012
Selecting the target year
Preliminary Research of Regenerative Cooling Channel Design for Small Scale Bipropellant Thruster
Jang, Dong-Wook ; Jo, Sung-Kwon ; Cho, Hwang-Rae ; Bang, Jeong-Seok ; Kwon, Se-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 2, 2012, Pages 1~9
DOI : 10.6108/KSPE.2012.16.2.001
Applicability of regenerative cooling in 2,500 N-class bipropellant thruster using hydrogen peroxide and kerosene was considered for improvement of performance and application in various missions. Calculation was performed by one dimensional approach using hydrogen peroxide as a coolant. The heat flux of thruster at nozzle throat was estimated at 18 - 20 MW/
. Designed cooling channel width and height were 2.5 mm and 0.5 mm, respectively. Based on designed cooling channel configuration, flat plate model was manufactured and tested for estimation of pressure drop in cooling channel, and CFD analysis was compared with the test result. The maximum error between CFD analysis and experimental result was approximately 13% and average error was approximately 5%.
Performance Analysis and Configuration Design of the Thruster Nozzle for Ground-firing Test and Evaluation
Kam, Ho-Dong ; Kim, Jeong-Soo ; Bae, Dae-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 2, 2012, Pages 10~16
DOI : 10.6108/KSPE.2012.16.2.010
A computational analysis of nozzle flow characteristics and plume structure is conducted to examine performance of the supersonic nozzle employed in a thruster for ground firing test. At first, flow simulations in two-dimensional converging-diverging nozzle are performed for the verification of computational capability as well as turbulence model validity. Axisymmetric converging-diverging nozzles for ground firing test are analyzed with the k-
SST model. A performance penalty caused by flow separation in a diverging section is observed in initially-designed nozzle. The performance could be enhanced by the modification of the diverging section of nozzle contour.
A Study on the Isomerization Reactions of Tricyclopentadiene Derivatives Using Aluminum Chloride(AlCl
Jo, Hyun-Hye ; Kwon, Tae-Soo ; Park, Chang-Sun ; Han, Jeong-Sik ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 2, 2012, Pages 17~24
DOI : 10.6108/KSPE.2012.16.2.017
Tetrahydrotricyclopentadiene(below THTCPD) isomer is a good candidate materials for the high performance liquid fuel component because of its high density and heat of combustion value. The object of this study was to find out the proper reaction condition to improve the fluidity of THTCPD which is solid state at room temperature. Therefore, we have carried out isomerization reactions using aluminum chloride in the varying reaction condition such as reaction temperature and solvents. The results showed that when using aluminum chloride catalyst, THTCPD isomerization reaction was more active in the polar halogenated reaction media such as dichloromethane(methylene chloride: MC), 1,2-dichloroethane(ethylene chloride: EC) and chloroform than in non-polar hydrocarbon media such as n-Hexnae and toluene and was effected by reaction temperature variation.
Design Optimization of Liquid Rocket Engine Using Genetic Algorithms
Lee, Sang-Bok ; Lim, Tae-Kyu ; Roh, Tae-Seong ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 2, 2012, Pages 25~33
DOI : 10.6108/KSPE.2012.16.2.025
A genetic algorithm (GA) has been employed to optimize the major design variables of the liquid rocket engine. Pressure of the main combustion chamber, nozzle expansion ratio and O/F ratio have been selected as design variables. The target engine has the open gas generator cycle using the LO2/RP-1 propellant. The gas properties of the combustion chamber have been obtained from CEA2 and the mass has been estimated using reference data. The objective function has been set as multi-objective function with the specific impulse and thrust to weight ratio using the weight method. The result shows about 4% improvement of the specific impulse and 23% increase of the thrust to weight ratio. The Pareto frontier line has been also obtained for various thrust requirements.
The Study of Aerodynamic Characteristics of Jet-Vane Affected by the Shroud
Park, Soon-Jong ; Park, Jong-Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 2, 2012, Pages 34~41
DOI : 10.6108/KSPE.2012.16.2.034
Thrust vector control system is a control device which is mounted on the exit of the nozzle to generate pitch, yaw and roll directional force by deflecting flow direction of the supersonic jet from the nozzle. Thermal and aerodynamic loads are acting on the surface of jet vane when it is exposed to the jet flow. Axial thrust loss and side thrust loss are affected by shock patterns and interactions between jet-vanes which varies with jet-vane geometry and turning angle. In this research, the performance estimation using the numerical simulation analysis of the nozzle is given and the investigation of the flow visualization and aerodynamic performance with the enforced power to the vane is taken.
Comparative Studies of Heat Transfer Coefficients for Rocket Nozzle
Hahm, Hee-Cheol ; Kang, Yoon-Goo ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 2, 2012, Pages 42~50
DOI : 10.6108/KSPE.2012.16.2.042
The goal of heat transfer studies is the accurate prediction of temperature and heat flux distribution on material boundaries. To this purpose, general-purpose computational fluid dynamics(CFD) code is used : FLUENT. Mass fluxes and pressure ratio are calculated for two types of nozzle. The comparative studies reveal that the computational results are in agreement with the experimental data. Also, heat transfer coefficients from FLUENT for one type of nozzle are very similar and agree well with the experimental data in the diverging part of the nozzle, but the calculated results are large in the converging part. The heat transfer coefficients from Bartz equation are over-predicted. We can consider various reasons for these differences, i.e., laminarization by the highly accelerated flow in the nozzle, turbulent flow model and grid generation.
Control of the Base Pressure of the Supersonic Jet Using an Orifice
Lee, Jong-Sung ; Kim, Heuy-Dong ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 2, 2012, Pages 51~57
DOI : 10.6108/KSPE.2012.16.2.051
Base pressure at the base of high-speed jet has long been one of the important issues from both the view points of fluid dynamics as well as practical engineering applications. The base pressure characteristics of incompressible flows have been well known to date. However, the base pressure at transonic or supersonic speeds would be different due to the compressibility effects and shock waves. In the present paper, a CFD study has been performed to understand the base pressure characteristics at transonic and supersonic speeds, prior to experimental work. An emphasis is placed on the control of the base pressure using a simple orifice. A variety of supersonic jet plumes have been explored to investigate the flow variables influencing the base pressure. The results obtained were validated with existing experimental data and discussed in terms of the base pressure and discharge coefficient of the orifice.
Experimental Study on the Flow Hysteresis Phenomenon in a Supersonic Nozzle
Nam, Jong-Soon ; Kim, Heuy-Dong ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 2, 2012, Pages 58~64
DOI : 10.6108/KSPE.2012.16.2.058
Hysteresis phenomena in fluid flow systems are frequently encountered in many industrial and engineering applications and mainly appear during the transient processes of change of the pressure ratio. Shock-containing flow field in supersonic nozzles is typically subject to such hysteresis phenomena, but associated flow physics is not yet understood well. In the present study, experimental work has been carried out to investigate supersonic nozzle flows during the transient processes of change in the nozzle pressure ratio. Time-dependent surface wall pressures were measured by a multiple of pressure transducers and the flow field was visualized using a nano-spark Schlieren optical method. The results obtained show that the hysteresis phenomenon is strongly dependent on the nozzle geometry as well as the time scale of the change of pressure ratio.
Development of Ultrasonic Defect Analysis Program for a Composite Motor Case
Kim, Dong-Ryun ; Lim, Soo-Yong ; Chung, Sang-Ki ; Lee, Kyung-Hoon ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 2, 2012, Pages 65~72
DOI : 10.6108/KSPE.2012.16.2.065
A defect analysis program for a composite motor case was developed to apply the ultrasonic signal processing method, based on the ultrasonic pulse-echo method. With the proposed defect analysis program, defects of FRP delamination and FRP/Rubber disbond in the composite motor case could be quantitatively measured. The defects detected in the composite motor case were in good agreement with the results measured with the computed tomography and video microscope. This paper described the development process of the defect analysis program to convert the ultrasonic test data into the C-Scan images.
Ablation Characteristic Study for Carbon Fabric/EPDM Chamber Insulation
Kim, Jin-Yong ; Choi, Ji-Yong ; Rho, Tae-Ho ; Lee, Won-Bok ; Cho, Won-Man ; Hahm, Hee-Cheol ; Yun, Nam-Gyun ; Rhee, Young-Woo ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 2, 2012, Pages 73~79
DOI : 10.6108/KSPE.2012.16.2.073
We developed the carbon fabric/EPDM chamber insulation in order to protect motor case with high intensity gas flow. A six-inch simulation motor connected with extension tube was designed to test ablation characteristic of insulation. High intensity gas flow was induced by a FRP disc with hole between motor and extension tube. After ground test, ablation depth of the carbon fabric/EPDM insulation was decreased compared to another insulations after ground static test.