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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 18, Issue 6 - Dec 2014
Volume 18, Issue 5 - Oct 2014
Volume 18, Issue 4 - Aug 2014
Volume 18, Issue 3 - Jun 2014
Volume 18, Issue 2 - Apr 2014
Volume 18, Issue 1 - Feb 2014
Selecting the target year
Analysis of the Theoretical Performance Characteristics for Methane-fuel Bipropellant Rocket Engine
Kim, Jong Hyun ; Jung, Hun ; Kim, Jeong Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 3, 2014, Pages 1~7
DOI : 10.6108/KSPE.2014.18.3.001
A set of preliminary design parameters for the bipropellant rocket engine using liquid methane-fuel as green propellant were derived through a theoretical performance analysis. Chemical equilibrium analysis utilizing CEA was conducted for the prediction of combustion performance: combustion characteristics according to the O/F ratio and chamber pressure variation were investigated. For a determination of chamber-characteristic length, the vaporization time of fuel-droplet with various performance parameters was calculated by applying Spalding`s 1-D droplet vaporization model. Finally, the preliminary design specification of methane-bipropellant rocket engine, which is to be performance-tested under the ground firing condition, was proposed.
Investigation of the Intake Stability of Bank-to-Turn Supersonic Missile under Sideslip Angle Based on CFD Analysis
Park, Jungwoo ; Park, Iksoo ; Jin, Sangwook ; Park, Keunhong ; Hwang, Kiyoung ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 3, 2014, Pages 8~16
DOI : 10.6108/KSPE.2014.18.3.008
This paper analyzes the effects of sideslip angle(SA) on the buzz margin of supersonic intake. The buzz margin is assumed to be stabilized by a controller which generates command depending only on the longitudinal sensor measurements. The analysis is performed based on three dimensional CFD results with which the sensor measurements can be simulated. In such a control system based on the longitudinal measurements, unexpected lateral flow perturbation results in the increase in the total angle of attack(TAoA), that causes the degradation of the engine intake performance. As a consequence, it is shown that the control stability is reduced such that additional control margin needs to be secured.
Estimation of Storage Life for Propellant Bag by Using Gamma Process Model
Park, Sungho ; Kim, Jaehoon ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 3, 2014, Pages 17~25
DOI : 10.6108/KSPE.2014.18.3.017
The purpose of this paper is to present a method to estimate the storage life of propellant bag for degradation of breaking load with storage time by using gamma process model. The nitrogen compound generated by natural decomposition of propellants degrades the breaking load of propellant bag with time. The statistical distributions of condition and lifetime with time were shown from the results of accelerated life test of propellant bag cloth at
. It was found that the use of median for life was highly appropriate and the
life should be selectively applied to the quality assurance policy.
Visualizations of Gas-centered Swirl Sprays in Sub to Super Critical Conditions
Kim, Dohun ; Lee, Keonwoong ; Son, Min ; Koo, Jaye ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 3, 2014, Pages 26~33
DOI : 10.6108/KSPE.2014.18.3.026
The gas-centerd swirl injectors are widely used on the main combustor of large liquid propellant rocket engines. Since the gas-liquid propellants, such as kerosene and oxygen-rich gas combination, are mixed and burned in the high pressure condition over the critical pressure point, the cold-flow spray test in the atmospheric condition can not represent the actual spray pattern. To observe the near actual spray patterns of gas-centered swirl injector, the high pressure spray chamber and the control system were constructed. The operating sequence was controlled precisely to obtain clear visualization images.
Numerical Study for Design of Center-body Diffuser
Kim, Jong Rok ; Kim, Jae-Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 3, 2014, Pages 34~39
DOI : 10.6108/KSPE.2014.18.3.034
A study is analyzed on the design factor of center-body diffuser and performed on conceptual design of center-body diffuser with computational fluid dynamic. The flow field of center-body diffuser is calculated using axisymmetric two-dimensional Navier-Stokes equation with
turbulencemodel. The center-body diffuser is compared with second throat exhaust diffuser in terms of starting pressure, the degree of vacuum pressure and the design factors. The counter flow jet on cone-tip of the center-body is applied for thermal protection system in the center-body diffuser.
Study on Solid Propellant Grain Burn-back Analysis Using Analytical Method
Sohn, Jihyun ; Jang, Jinsung ; Oh, Seokhwan ; Roh, Taeseong ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 3, 2014, Pages 40~47
DOI : 10.6108/KSPE.2014.18.3.040
The grain burn-back analysis has been performed for the internal ballistics analysis code to be used for the optimal design of the space launch vehicles. The grain burn-back has been used to calculate the burning surface that is essential to the internal ballistics. The calculation of internal ballistics code used in the optimal design is repeated until satisfying the required performance through the change of the design parameter. Therefore, the burn-back method applied to the internal ballistics analysis should be easy to change the design parameter and calculation time should be short. In this study, a burn-back analysis code has been developed using the analysis method. Also, geometric parameters of the grain have been selected and organized. The developed code has been verified by comparison of results of a numerical method.
Design and Hot Fire Tests of the Pyrostarter for Liquid Rocket Engines
Kang, Sang Hun ; Jang, Jesun ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 3, 2014, Pages 48~55
DOI : 10.6108/KSPE.2014.18.3.048
In present study, design and hot fire tests of the pryostarter are conducted. To prevent the turbopump RPM overshoot, regressive mass flow rate profile is applied. Sudden decrease of the mass flow rate at the end of the propellant burning is realized as well. Firing test results show good agreements with the design requirements. Through the study with ignition substance variations, combustion products and ignition performances are improved.
Analysis of Internal Ballistic Characteristics of Solid Rocket with Erosive Burning
Cho, Mingyoung ; Kim, Jinyong ; Park, Sunghan ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 3, 2014, Pages 56~61
DOI : 10.6108/KSPE.2014.18.3.056
Two erosive burning models were applied to compare analysis results of ballistic for the internal ballistics of solid rocket motors. By comparing motor tests with results of analysis, the variance of a grain shape was analyzed and coefficients of erosive burning were drawn. Results of comparison presents that the coefficient of erosive burning was proportional to the change of burning area, while inversely proportional to the change of cross area.
Conceptual Study of an Exhaust Nozzle of an Afterburning Turbofan Engine
Choi, Seongman ; Myong, Rhoshin ; Kim, Woncheol ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 3, 2014, Pages 62~69
DOI : 10.6108/KSPE.2014.18.3.062
This paper presents a preliminary study of a convergent divergent nozzle in an afterburning turbofan engine of a supersonic aircraft engine. In order to design a convergent divergent nozzle, cycle model of a low bypass afterburning turbofan engine of which thrust class is 29,000 lbf at a sea level static condition is established. The cycle analysis at the design point is conducted by Gasturb 12 software and one dimensional gas properties at a downstream direction of the turbine are obtained. The dimension and configuration of an model turbofan engine are derived from take-off operation with wet reheat condition. The off-design cycle calculation is conducted at the all flight envelope on the maximum flight Mach number of 2.0 and maximum flight altitude of 15,000 m.
Development of the Korean 2.75 inch Rocket Propulsion System
Kang, Kiha ; Lee, Yongbum ; Yeom, Yongyeol ; Bang, Gibok ; Yang, Youngjun ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 3, 2014, Pages 70~77
DOI : 10.6108/KSPE.2014.18.3.070
In this paper, the development of unique model of the 2.75 inch rocket propulsion system is described. Recently developed korean 2.75 inch rocket propulsion system shows the improvement of a flame stability resulted from a change in the configuration of propellant grain, and of an incidental ignition protection function using the EMI(electromagnetic interference) filter on ignition system. Moreover it is shown that a directional flight stability is improved by increasing the number of fins and changing the nozzle configuration. Static firing test and thermal shock test were conducted for the validation before flight, and flight test of 210 rounds of rockets was conducted to verify the trajectory uniformity. In addition, intellectual property issues can be overcome with the unique korean 2.75 inch rocket motor as well as the performance improvement.
Analysis of a Flow Passage Opening Device using RecurDyn
Jung, Sungmin ; Kim, Young Shin ; Park, Jeong-Bae ; Jun, Pil Sun ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 3, 2014, Pages 78~83
DOI : 10.6108/KSPE.2014.18.3.078
A special part such as a flow passage opening device is required to prevent the disconnection of fuel transfer in a pressurized fuel tank. To meet this requirement, the device utilizing an acceleration follow-up technique was invented. RecurDyn, a dynamic analysis tool, is introduced in this article to predict the device`s performance and to determine parameters affecting it. In the analysis, it is shown that balancing weights can open the passage in accordance with fuel position.
Flow Control Characteristics of Cavitating Venturi in a Liquid Rocket Engine Test Facility
Kang, Donghyuk ; Ahn, Kyubok ; Lim, Byoungjik ; Han, Sanghoon ; Choi, Hwan-Seok ; Seo, Seonghyeon ; Kim, Hongjip ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 3, 2014, Pages 84~91
DOI : 10.6108/KSPE.2014.18.3.084
The flow rate control of a cavitating venturi has been investigated with downstream pressure variation. A set of cavitating venturies for a liquid rocket engine thrust chamber firing test facility have been designed and manufactured. The flow characteristics of the cavitating venturies have been analyzed by experimental and computational methods. Results showed that constant mass flow rate condition was established by the cavitation inside the venturi. However, upstream pressure less than the actual design pressure of the cavitating venturi could not supply a constant flow rate.