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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
Editor in Chief :
Volume & Issues
Volume 8, Issue 4 - Dec 2004
Volume 8, Issue 3 - Sep 2004
Volume 8, Issue 2 - Jun 2004
Volume 8, Issue 1 - Mar 2004
Selecting the target year
An Experimental Study on the Flow Characteristics of a Supersonic Turbine Cascde as Nozzle Installation Angle
Cho Jong-Jae ; Jeong Soon-In ; Kim Kui-Soon ; Park Chang-Kyu ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 4, 2004, Pages 1~8
In this paper, a small supersonic wind tunnel is designed and built to study the flow characteristics of a supersonic impulse turbine cascade. The flow is visualized by means of a sin91e pass Schlieren system. The supersonic cascade with 3-dimensional supersonic nozzle was tested over a wide range of nozzle installation angle. Highly complicated flow patterns including shocks, nozzle-cascade interaction and shock boundary layer interactions are observed.
The Computation of True Thrust Using only the Measured Thrust
Kim Jun-Yeop ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 4, 2004, Pages 9~15
The measured thrust could be distorted because of the transient response of thrust stand during combustion of rocket motor. As a result of the distorted thrust, it is not easy for us to know the values of thrust peak and thrust duration time. Therefore, it is of great importance to compute the true thrust from the measured thrust. In this study the method to eliminate the transient response from the measured thrust using only the measured thrust was Proposed, and also experimental data were used to approve the proposed method. The result showed that the proposed method would be available to compute the true thrust.
Theoretical Analysis on the Heat Transport Limitation of a Sintered Metal Wick Heat Pipe
Kim Keun-Bae ; Kim Yoo ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 4, 2004, Pages 16~25
Theoretical analysis for predicting the heat transport limitation of a copper powder sintered wick heat pipe was performed. The heat pipe diameter was 8mm and water was used for working fluid. The particle diameter was classified by 5 different meshes, and each capillary pressures and heat transport limitations. thermal resistances were analyzed according to the operating temperatures, wick thicknesses and inclination angles, based on the effective capillary radius(
), Permeability (K). The wick capillary limitation was increased according as the particle diameter and the wick thickness and the operating temperature were increased. As the porosity and the capillary radius were larger. then the heat transport limitation was higher. The thermal resistance was greatly increased according as the wick thickness was increased.
Low Frequency Dynamic Characteristics of Liquid-Propellant Rocket Engine Turbopump
Ha Seong-Up ; Jung Young-Seok ; Han SangYeop ; Oh Seung-Hyub ; Kim Young-Mog ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 4, 2004, Pages 26~35
As part of thrust control technology research on turbopump-fed type liquid-propellant rocket engine system, the low frequency dynamic characteristics of turbopump was investigated. It can be described that a turbopump system has a 1st-order lag element. When the value, which was resulted by subtraction of the variation of turbine moment with respect to the variation of revolution number from the variation of pump moment with respect to the variation of revolution number, was positive, the time constant of the 1st-order lag element was positive which stood for a stable system. Increasing the above-mentioned valve within positive range leaded to the increase of response and to the decrease of controllability.
The Structural Design for Combustor Chamber of Liquid Rocket Engine
Chung Yong-Hyun ; Ryu Chul-Sung ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 4, 2004, Pages 36~42
The Properties of material, C18200 which is used for development of high performance liquid rocket engine combustor chamber were obtained by tension tests. The specimen for regenerative combustor was designed by structural analysis using that Properties. After the designed specimen was manufactured by the same manufacturing process of regenerative combustor. the yielding stress and yielding strain were obtained by strength tests. The properties of C18200 was degraded very much after brazing. The estimation of yielding pressure by structural analysis was almost same as that of strength test. The collector Part was yielded and failed previously than that of cooling channel part during strength test.
Visualization Study on the Phase Difference of a Dragonfly Type Wing
Kim Hyun Seak ; Kim Song Hak ; Chang Jo Won ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 4, 2004, Pages 43~54
A visualization study was carried out to investigate the effects of phase difference qualitatively by examining wake pattern on the phase difference of a dragonfly type wing model. The model was built with scaled-up, flapping wings composed of a paired wing with fore- and hind-wings in tandem that mimick the wing form of a dragonfly. The present study was conducted by using the smoke-wire technique and an electronic device below the tandem wings was mounted to find the exact wing position angles. Uncertainties in wing position angle are about
and instantaneous wing positional angle varies from
. The tests were made at phase differences between the fore-wing and hind-wing at
. The results show that Karman vortex structures were produced at phase differences of
, but Karman vortex structures were not observed at the phase difference of
Acoustic, Entropy and Vortex Waves in a Cylindrical Tube With Variable Section Area
Cho Gyu-Sik ; Lebedinsky Ev. V ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 4, 2004, Pages 55~66
In this paper a method for finding solutions of acoustic, vortex and entropy wave equations in a cylindrical tube with variable section area was suggested under the consideration of that the high frequency instability in a rocket engine combustion chamber is an acoustic phenomena, which Is coupled with combustion reaction. and that a combustion chamber and exhaust nozzle are usually shaped cylindrically As a consequence of that some method. which enable the mathematical analysis of the influence of entropy and vortex waves to acoustic wave. was suggested. According to the method reflection coefficients of acoustic wave on a supercritical nozzle was numerically calculated, through which it was presented that entropy or vortex waves can strengthen or weaken the reflection rate of acoustic wave.
Transient Analysis of a Liquid Rocket Engine System Considering Thrust Control
Park Soon-Young ; Choi Hwan-Seok ; Seol Woo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 4, 2004, Pages 67~75
It is essential to develop a transient analysis model for the turbopump-fed type liquid rocket engine development, especially for deriving the number of test and its parameters. In this study we proposed a mathematical model of turbopump-fed type liquid rocket engine, and inspected transient mode changes of a rocket engine according to variations of thrust control valve opening ratio. To verify the results, we solved the same problem with AnaSyn software from Russia, and concluded that the results of transient code we developed deviated within 2% from AnaSyn results. Also, using the transient engine analysis code we showed the possibility to find out the system level design Parameters of the components. For example, we modeled a pressure stabilizer which is used to control the consistency of mixture ratio in the gas generator as forced damping system, and found the stability range of the natural frequency and the damping ratio with the transient engine system analysis code.
Dynamic Performance Simulation of the Propulsion System for the CRW-Type UAV Using SIMULINK
Kong Chang-Duk ; Park Jong-Ha ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 4, 2004, Pages 76~83
A Propulsion System of the CRW(Canard Rotor Wing) type UAV(Unmanned Aerial Vehicle) was composed of the turbojet engine to generate the propulsive exhaust gas, and the duct system including main and rotary ducts, the nozzle subsystem including main and tip jet nozzle for three flight modes such as lift/landing mode, low speed transition flight mode and high speed forward flight mode. Transient simulation performance utilized the ICV (Inter-component volume) method and simulated using the SIMULINK. Transient performance analysis was performed on 3 cases. Fuel flow schedules to accelerate from Idle to maximum rotational speed were divided into the step increase of the most severe case and ramp increase cases to avoid the overshoot of turbine inlet temperature, and variations of thrust and the turbine inlet temperature were investigated in some transient analysis cases.
Hot-Fire Test and Performance Evaluation of Small Liquid-Monopropellant Thrusters under a Vacuum Environment
Kim Jeong Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 4, 2004, Pages 84~90
A performance evaluation is made in terms of thrust, impulse bit. and specific impulses for a set of mono-propellant hydrazine thrusters producing 0.95 lbf of nominal thrust at an inlet pressure of 350 psia. With a brief description on the hot-firing test configuration and procedures. a typical data obtained from steady-state firing mode is given directly showing the variational behavior of propellant supply pressure, mass flow rate, vacuum condition, and thrust. The performance features are successfully compared to the reference criteria of 1-lbf standard mono-propellant rocket engine. Additionally. a statistical inter-thruster treatment is concisely depicted for the justification of selected thrusters as a grouped member of flight model for spacecraft propulsion system.
Low Frequency Dynamic Characteristics of Liquid-Propellant Rocket Engine Combustor
Ha Seong-Up ; Jung Young-Seok ; Kim Hui-Tae ; Han SangYeop ; Cho Gwang-Rae ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 4, 2004, Pages 91~101
With the mathematic linear model of a combustor which consists of a combustion chamber and injectors, the analysis of low frequency dynamic characteristics of a liquld-propellant rocket engine combustor was performed. Propellant mass flowrate was varied by combustion chamber pressure feedback, therefore low frequency oscillation was appeared. Increasing the time constant of a combustion chamber and injector pressure differences and decreasing combustion time delay increased the combustor system stability. The variation of injector time constant little affected stability. The system was always stable, when there was no combustion time delay. Increasing combustion time delay decreased oscillation frequency and damping ratio, and the system eventually became unstable.
A Study for Liquid Rocket Engine System Layout and Assembly
Ryu Chul-Sung ; Chung Yong-Hyun ; Oh Myung-Hwan ; Nam Kyoung-O ; Moon Jong-Hoon ; Seol Woo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 4, 2004, Pages 102~108
A layout of regenerative liquid rocket engine using turbo pump has been designed for development of high performance liquid rocket engine. each components of engine system was placed by considering assembly and characteristic. first stage engine system is controled by one plane of axis gimballing and composed of four engine assembly to cluster with launch vehicle. second stage engine system is controled by two plane of axis gimballing and composed of one engine assembly. assembly and disassembly Processes and required program have been developed. various shape of instruments were also developed for carrying out assembly and disassembly process efficiently.
Numerical Investigation of Flowing Process for Regenerative Beat Exchanger of a Gas Turbine Engine
Kim Soo Yong ; Kovalevsky Valeri P ; Goldenberg Victor ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 4, 2004, Pages 109~121
A distributed nonlinear mathematical model for investigation of regenerative heat exchangers of both a continuous and periodic operation is described in the paper. The non-iterative numerical integration scheme for conjugate unsteady heat exchange problem of one dimensional flows and two dimensional matrix wall conductivity is developed. Case study of a regenerative heat exchanger with a rotary ceramic matrix is presented. The range of optimum rotation rates of the regenerator providing the greatest calorific efficiency is determined.