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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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Journal of the Korean Society of Propulsion Engineers
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Journal DOI :
The Korean Society of Propulsion Engineers
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Volume & Issues
Volume 10, Issue 4 - Dec 2006
Volume 10, Issue 3 - Sep 2006
Volume 10, Issue 2 - Jun 2006
Volume 10, Issue 1 - Mar 2006
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A Numerical Study on Bituning of Acoustic Resonator in a Combustion Chamber of Liquid Rocket Engine
Lee Su-Ryong ; Sohn Chae-Hoon ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 1, 2006, Pages 1~8
A linear acoustic analysis is conducted to examine bituning of acoustic resonators for acoustic damping in a combustion chamber of liquid rocket engine. Bituned resonators are tuned to the two principal modes, the first tangential(1T) and the first radial(1R) modes. First, the acoustic-damping effect of monotuned resonators is investigated. The damping capacity is quantified by damping factor as a function of the number of the resonators monotuned to 1T or 1R mode. Next, the damping characteristics of the bituned resonators are investigated. From the numerical data, the number of resonators, to be tuned to 1T and 1R modes, respectively, can be selected properly. Furthermore, the concept of resonator bituning is applied to reduce the degradation of damping effect caused by the mode split and thereby, optimal bituning frequencies are found.
Design Method of the High Accuracy Thrust Stand
Lee Kyu-Joon ; Park Ik-Soo ; Choi Yong-Kyu ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 1, 2006, Pages 9~17
The thrust measurement systems(TMS) with high accuracy are required in rockery, according to develop the high precise guided space vehicle. For obtaining high accuracy, the basic concepts and the necessary technology which have been acquired through many experiences of TMS are summarized, and the design methodology for practical use in ADD is presented. In this paper, the parameters against accuracy of TMS are discussed, and the improving methods are suggested. Through this application example, the design methodology of ADD is shown its superiority in TMS.
Hydrodynamic Performance Test of a Turbopump
Hong Soon-Sam ; Kim Dae-Jin ; Kim Jin-Sun ; Choi Chang-Ho ; Kim Jin-Han ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 1, 2006, Pages 18~22
Hydrodynamic performance test was conducted for a fuel pump of a liquid rocket engine turbopump. The pump driven by an electric motor was tested using water. It is experimentally shown that the inducer had very small effect on the pump's head and efficiency but great effect on the pump's cavitation performance. Additionally, inducer test was carried out to investigate the effect of the inducer on the pump in detail, and it was found that the pump reached a critical cavitation number when the inducer head dropped by 55%.
Theoretical Analysis of Annular Injection Supersonic Ejector with a Simple Funnel Shock Wave Model
Kim Se-Hoon ; Kwon Se-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 1, 2006, Pages 23~29
In an annular injection supersonic ejector, the supersonic primary flow is injected along the side wall, therefore a funnel-shaped shock wave is generated by the contraction angle of the mixing chamber. In the present study, we developed a simple funnel shock wave model using 2-D wedge and conical shock wave relations. In result, the secondary flow pressure can be predicted more accurately than using a simple 2-D wedge shock wave model. Through the same analysis, the compression ratio and the adiabatic efficiency according to the entrainment ratio were calculated.
A Study on the Thermal Response Characteristics of Carbon/Carbon Composites for Nozzle Throat Insert
Ham Hee-Cheol ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 1, 2006, Pages 30~37
A thermal resistance estimation of carbon/carbon composites used as the nozzle throat insert of solid rocket motor was performed using TPEM motor. Three types of TPEM motor and two types of propellant were employed. The ablation rate is higher for the higher chamber pressure and also higher for the higher concentration of oxidizing species in combustion gas, but it is lower for the higher material density.
Study on Preliminary Design of Fuel Transfer Jet Pump Using SIMULINK
Kong Chang-Duk ; Park Jong-Ha ; Han Dong-Joo ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 1, 2006, Pages 38~43
In the present study, preliminary design and analysis for a jet pump, which is able to transfer fuel from the tank to the engine, were performed as an aerospace component technology development project. The jet pump is a core part, which is normally installed in the fuel tank, to supply the fuel from the tank to the engine feed pump, or to transfer the feed between tanks. In order to design preliminarily installed in the jet pump, equations for design were modelled using SIMULINK, and the design was carried out based on the simulation model.
Density Profile Evaluation of Needle-punched Carbon/Carbon Composites Nozzle Throat by the Computed Tomography
Kim Dong-Ryun ; Yun Nam-Gyun ; Lee Jin-Yong ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 1, 2006, Pages 44~53
In this study, the non-destructive computed tomography was adopted to observe the density profile of the needle-punched Carbon/Carbon(C/C) composites nozzle throat. The density profile of C/C was evaluated within
with 98.74% confidence when the correction of the image and high signal-to-noise ratio were achieved by the optimization of the beam hardening, the electrical noise and the scattered X-ray. The density variation of C/C with the computed tomography was in good agreement with the results obtained by the water immersion method and the observation with scanning electron microscope.
A Study On the Ejector Design Technique And Flow Characteristics
Lee Yang-Ji ; Cha Bong-Jun ; Yang Soo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 1, 2006, Pages 54~63
Ejector system are used to transport a low momentum flow to the higher pressure flow by the momentum change between high and low momentum flows. This system is used to simulate the high altitude and Mach number condition over altitude 20 km and Mach 4 of the supersonic test facility. We applied the design and the performance analysis technique(EISIMP code) of the Ramjet Test Facility(RJTF) air system in JAXA to the ejector system of the ramjet test facility in KARI. After preliminary design of the ejector system, we performed a computational study using FLUENT and investigated shock structures and flow characteristics of the ejector system.
Technical Review of the Proposed Engines for SUAV
Jun Yong-Min ; Yang Soo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 1, 2006, Pages 64~71
For SUAV is required to have the capacity of VTOL and fast forward flight, the SUAV development program has decided to adopt the tiltrotor mechanism which includes helicopter and turboprop mechanisms. From the engine point of view, the key engine parameters such as engine operating mechanism, engine control scheme, the dynamics characteristic of power train, engine intake/exhaust concept, and engine installation requirements should fulfill the requirements of the two different mechanisms, helicopter and turboprop. And for the maximum efficiency of the rotor, rotational speed for the two modes are 20% different, the power train shall find a way to make it so. Meeting these specific requirements for the tiltrotor mechanism, this research begins with a conventional OTS(off-the-shelf) turboshaft engine survey and minimizes engine modification to develop an economical propulsion system. The engine technical review has been performed on the basis of those requirements and capabilities.
Technical Review and Analysis of Ramjet/Scramjet Technology I. Ramjet Engine (Liquid Ramjet, Ducted Rocket)
Sung Hong-Gye ; Yoon Hyun-Gull ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 1, 2006, Pages 72~86
A technical review of current ramjet propulsion is presented. In addition to summarize the current status of ramjet technology, new key techniques like Boosting technique easily adapting total impulse of booster, flame stabilization technique with minimized ramjet combuster length, variable nozzle-inner-surface technique realizing wide flight-envelop, and thermal protection technique for long operating time are identified. Actually various Ramjet propulsion technology has been matured and expanding to both military and combined cycle application. Yet many opportunities remain to be challenged by future generations of explorers to utilize s typical ramjet propulsion system for multi-purpose(multi-platform and multi-target) missiles, for example, American JSSCM and Russian Yakhont missiles, improving both reliability of techniques and downsizing development cost of new propulsion system.