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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 10, Issue 4 - Dec 2006
Volume 10, Issue 3 - Sep 2006
Volume 10, Issue 2 - Jun 2006
Volume 10, Issue 1 - Mar 2006
Selecting the target year
Spray Characteristics of a Liquid-Liquid Swirl Coaxial Injector Part I : Effect of Injection Condition
Kim, Dong-Jun ; Im, Ji-Hyuk ; Han, Poong-Gyoo ; Yoon, Young-Bin ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 3, 2006, Pages 1~8
The influences of injection conditions and recess configuration of liquid-liquid swirl coaxial injectors on spray characteristics were investigated. The characteristics of the coaxial spray in internal mixing injection region were mainly controlled by the merging phenomenon and momentum balance between two liquid sheets, but those in internal mixing injection region were influenced by the impingement phenomenon as well as momentum balance between two liquid sheets.
Spray Characteristics of a Liquid-Liquid Swirl Coaxial Injector Part II : Effect of Recess Configuration
Kim, Dong-Jun ; Kim, Sung-Hyuk ; Han, Poong-Gyoo ; Yoon, Young-Bin ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 3, 2006, Pages 9~17
The influences of recess length of a liquid/liquid swirl coaxial injector on spray characteristics were investigated. It was revealed that the internal impinging phenomenon played an important role in the spray characteristics, such as spray angle and breakup length. Also, as the recess length increased, the mean drop size increased due to the increase of effective film thickness and mixing efficiency increased, but in the case of very deep recess length, the mixing efficiency decreased.
Development of Automatic Design Program for Solid Rocket Motors Structure
Kim, Won-Hoon ; Koo, Song-Hoe ; Moon, Soon-Il ; Hwang, Ki-Young ; Lee, Kang-Soo ; Seok, Jung-Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 3, 2006, Pages 18~25
In order to perform system requirements quickly and accurately, an automatic design program of solid rocket motors(SRM) structure designated as the 'ProDes software' has been developed and verified. from given system design criteria and constraints, it has the capabilities to design, analysis, simulation and drawing process to greatly reduce the over 'design cycle time' and manpower of a project. The conception of the program is modular, and calculations are performed step by step allowing parametric design studies and providing final selected design goal. Each configurations of SRM components and joint types composed of various master models is obtained from the data base module of the library. Between the design results of the ProDes software and those of the previous detail design of the established motor showed good agreements.
Development of Prototype Fill/Drain Valve for Supply of Satellite Propellant
Kim, Su-Kyum ; Yu, Myoung-Jong ; Lee, Kyun-Ho ; Choi, Joon-Min ; Jang, Ki-Won ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 3, 2006, Pages 26~31
Through the KOMPSAT program, Koreanization of thruster have been carried out successfully, but there are still many difficulties in Koreanization of most core parts of propulsion system. Because the development of core parts is essential to participate in the advanced nations, KARI has carried out development of Fill/Drain valve for propellant/pressurant supply of satellite, which has high possibilities to be koreanized, with Hanwha Corp.. This paper summarizes overall processes of development including design, manufacturing and test, and finally 4 sets of modules were successfully made. Also the satisfaction of performance requirements are verified through performance tests.
An Application of Dynamic Radioscopy Technique to Static Firing Test
Lim, Soo-Yong ; Kim, Jun-Yeop ; Kim, In-Sik ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 3, 2006, Pages 32~40
Dynamic Radioscopy technique was developed to observe internal phenomena of motors during firings. For use of this technique, generator and image box consisting of conversion screen, mirror, and video camera were designed and fabricated at our laboratory, and static firing tests were conducted to small motors. Protection devices against vibration and noise induced from during combustion were also made and their performances were evaluated with reference to the vibration criteria. Test results have shown that the vibration levels at concerned points were measured less than vibration criteria, and the internal phenomena during firings were also observed clearly.
Effects of Mean Flow and Nozzle Damping on Acoustic Tuning of a Resonator in a Rocket Combustor
Sohn, Chae-Hoon ; Park, I-Sun ; Kim, Seong-Ku ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 3, 2006, Pages 41~47
Effects of mean flow and nozzle damping on acoustic tuning of a gas-liquid scheme coaxial injector are investigated numerically adopting a linear acoustic analysis. The injector plays a role as a half-wave acoustic resonator for acoustic damping in a combustion chamber of a liquid rocket engine. As Mach number of mean flow in a chamber increases, the resonant frequency of the first tangential mode decreases slightly and the optimum injector tuning length varies negligibly. Nozzle damping affects neither the resonant frequency nor the optimum length. From these numerical results, effects of mean flow and nozzle damping on acoustic tuning of a resonator are negligible. As open area of the injectors increases, the acoustic amplitude decreases, but new injector-coupled modes appear.
Test Method on Interlaminar Tensile Properties of Carbon fabric Reinforced Phenolic Composites
Lee, Ji-Hyung ; Kim, Hyoung-Geun ; Lee, Hyung-Sik ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 3, 2006, Pages 48~52
Through-the-thickness properties of thick-walled cylindrical composites are required to determine structural performances because interlaminar tensile stress is primarily responsible for structural failure of the composites during their curing process. It is necessary for evaluating the tensile properties to find individual test methods to find appropriate methods because there are no recognised international standards(test methods and test specifications) available for generating reliable tensile properties in the direction. This paper has performed an experimental study to measure that properties of carbon fabric/phenolic composites which are produced by domestic company. Several test methods using an aluminum specimen were compared and evaluated. The best test method to measure transverse through-the-thickness properties of composite materials was developed by the experimental results that strain trends on all faces of composite specimen are the same.
A Study on the External Insulation of Missile Surface
Park, Byeong-Yeol ; Ryoo, Moon-Sam ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 3, 2006, Pages 53~59
This paper presents the IR-Lamp test results of evaluating heat protection performance and measuring of mechanical/thermal properties in the heat protection material of missile external surface. The results showed that increasing the contents of microballoons improved the heat protection performance, but the mechanical properties were deteriorated. Among the kinds of microballoons, Epoxy/Phenolic Microballoons mixture showed the best mechanical properties and low thermal conductivity. Epoxy/Cork mixture showed the best heat protection in the IR-Lamp test, though it has low mechanical properties and high thermal conductivity.
Burning Rate Characteristics of Solid Propellant at Extremely High Pressure
Sung, Hong-Gye ; Yoo, Ji-Chang ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 3, 2006, Pages 60~66
Notable are the burning rate characteristics of solid propellant burning at extremely high pressure(10000-20000 psia). The burning rate test using closed bomb shows the discontinuous increment around 4000 psia so that the exponent of burning rate(n) is almost double, from 0.4 to 0.8. The pressure-increasing rate of the test motor is about 300 times as high as that of the motor operating at the conventional pressure, less than 2000 psia, is, therefor the burning rate is augmented about 5-50 times. The performance prediction reflecting the pressure-change-rate effect are fairly comparable with the test data at various test conditions.
Ignition of Solid Propellants at Subatmospheric Pressures
Kim, In-Cul ; Ryoo, Baek-Neung ; Jung, Jung-Yong ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 3, 2006, Pages 67~72
Several propellants were investigated experimentally for ignition characteristics in subatmospheric pressure. The threshold ignition pressure was 4 psia for HTPB/AP composite propellant. The partial replacement of AP in HTPB/AP propellant by
of HMX, HNIW showed that the improvements in ignition delay was over 50% and the threshold pressure was below 0.4 psia. This appears to be due to the characteristics of HMX and HNIW exothermic dissociated at the temperature(
) love. than that of AP. The ignition substance
was coated thinly on the propellant surface for better ignition performance. As a result, ignition delay time of 15% was improved. NC is applied to
ignition substance as a secondary binder and
suspension solution is coated to the propellant surface.
Functional Analysis of Flexure in a Captive Thrust Stand
Kim, Joung-Keun ; Yoon, Il-Sun ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 3, 2006, Pages 73~81
In order to evaluate the thrust of a propulsion system, generally the captive thrust stand is used Based on the applied propulsion system, the various captive ways between thrust stand and the propulsion system are considered. In this paper, the effect of motor deformation generated during firing in horizontal thrust stand on the measured thrust is theoretically derived from classical beam theory. New flexure performance index is defined and estimated on the basis of the thrust measurement error. Its result is good agreement with numerical result of ABAQUS. This study showed that measurement reliability and safety of test can be highly upgraded, in case of two flexure-type captive thrust stand.
A Study on Performance Diagnostics of Turbo-Shaft Engine For SUAV Using Gas Path Analysis
Lee, Eun-Young ; Roh, Tae-Seong ; Choi, Dong-Whan ; Lee, Chang-Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 3, 2006, Pages 82~89
Recently operation and maintenance cost of gas turbine engines has been issued as a major parameter in terms of designing and manufacturing. Accordingly, the conception that the maintenance and repair of an engine has to be conducted in assembled condition has been spreaded out. However, it is possible only if the prediction of the engine performance is clearly identified. In this study, therefore, a diagnostic code of the engine performance has been developed by using GPA(Gas Path Analysis) and Fuzzy Logic which can analyze the engine performance and estimate the health parameters. The prediction of the quantitative performance deterioration of the established model of the turbo-shaft engine for SUAV has been achieved in a satisfied level compared to that obtained by GSP code.
Experimental Investigation on Forced Convective Heat Transfer Characteristic Generated to Heated Tube
Park, Hee-Ho ; Lee, Yang-Suk ; Kim, Sun-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 3, 2006, Pages 90~98
The Heated Tube Facility(HIF) was fabricated to identify the forced convective heat transfer and the cooling characteristic for the hydrocarbon fuel(Jet A-1), which is used for the coolant of the regenerative cooling system. The forced convective heat transfer coefficient was calculated from the measured coolant and tube surface temperature. In case of using the Jet A-1, the maximum heat flux which the coolant can absorb was identified by determining the critical wall temperature generating the burnout on the fixed flow condition. The inlet bulk-temperature of the coolant has a direct influence on the forced convective heat transfer characteristic.
Modeling and Simulation of a Shape Memory Release Device
Lee, Yeung-Jo ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 3, 2006, Pages 99~108
Aerospace applications use pyrotechnic devices with many different functions. Functional shock, safety, overall system cost issue, and availability of new technologies, however, question the continued use of these mechanisms on aerospace applications. Release device is an important example of a task usually executed by pyrotechnic mechanisms. Many aerospace applications like satellite solar panels deployment or weather balloon separation need a release device. Several incidents, where pyrotechnic mechanisms could be responsible for spacecraft failure, have been encouraging new designs for these devices. The Frangibolt is a non explosive device which comprises a commercially available bolt and a small collar made of shape memory alloy (SMA) that replace conventional explosive bolt systems. This paper presents the modeling and simulation of Frangiblot by the change of bolt size and notch geometry. This analysis may contribute to improve the Frangibolt design.
Hot Firing Performance Measurement of Monopropellant Decomposition Catalyst and Domestic Development Status
Lee, Kyun-Ho ; Yu, Myoung-Jong ; Kim, Su-Kyum ; Jang, Ki-Won ; Cho, Sung-June ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 3, 2006, Pages 109~117
Hot firing performance test of hydrazine decomposition catalyst used for monopropellant thruster of satellite and launch vehicle was performed on the ground. A test equipment for hot firing performance measurement of catalyst test was developed in collaboration with Hanwha Corp., and the catalyst firing performance were tested with the equipment. After a reaction delay time, a catalyst activity and a granule stability were measured for 2 times, satisfactory results were obtained such as 25msec, 2%,
for each test items on the average. In addition, the current development status of domestic prototype catalyst and its decomposition performance test results are presented.