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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
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Volume & Issues
Volume 11, Issue 6 - Dec 2007
Volume 11, Issue 5 - Oct 2007
Volume 11, Issue 4 - Aug 2007
Volume 11, Issue 3 - Jun 2007
Volume 11, Issue 2 - Apr 2007
Volume 11, Issue 1 - Feb 2007
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Three-dimensional Numerical Analysis of Detonation Wave Structures in a Square Tube
Cho, Deok-Rae ; Won, Su-Hee ; Shin, Jae-Ryul ; Lee, Soo-Han ; Choi, Jeong-Yeol ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 1, 2007, Pages 1~10
Three dimensional structures of detonation waves propagating in a square tube were investigated using a high resolution CFD code coupled with a conservation equation of reaction progress variable and an one-step irreversible reaction. The code were parallelized based on domain decomposition technique using MPI library. The computations were carried on an in-house Windows cluster with AMD processors. Three-dimensional unsteady analysis results in the smoked-foil records caused by the instabilities of the detonation waves, which showed the rectangular and diagonal modes of detonation instabilities depending on the initial condition of disturbances and the spinning detonation for case of small reaction constant.
Effect of Combustion Chamber Design on Combustion Stability Characteristics of a Full-scale Gas Generator
Lee, Kwang-Jin ; Seo, Seong-Hyeon ; Han, Yeoung-Min ; Choi, Hwan-Seok ; Ahn, Kyu-Bok ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 1, 2007, Pages 11~17
Effects of combustion chamber design on combustion stability characteristics of a full-scale gas generator were studied experimentally. Thirty seven double-swirl injectors with recess number of 1.5 were distributed in the injector head, which significantly influences combustion performance. The characteristics of combustion stability were inspected by the parametric variations such as changing length and diameter of the combustion chamber and installing a turbulence ring. The experimental result shows that as the effective length of the combustion chamber decreased, an instability frequency took place in a high-frequency region, and the amplitude of the dynamic pressure generally diminished and could be reduced to the unharmful level. However, the dynamic pressure fluctuation in the region of longitudinal resonant frequency could not be suppressed perfectly.
Monopropellant Thruster with Monolith Support
An, Sung-Yong ; Jin, Jung-Kun ; Kwon, Se-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 1, 2007, Pages 18~26
A development of monopropellant thruster for microsatellite that uses concentrated hydrogen peroxide is described. Catalyst, the most important component in the thruster, was prepared and coated on a monolith honeycomb. Performance evaluation of thruster was peformed by considering the efficiency of characteristic velocity and ignition delay. As a result, 96.0% of
efficiency was obtained at designed propellant flowrate and steady state operating condition.
The Effects of Forming Depth and Lead Angle on Forming Force of Shear Spinning
Yeom, Sung-Ho ; Nam, Kyoung-O ; Park, Hyun-Jin ; Hong, Sung-In ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 1, 2007, Pages 27~33
The shear spinning has been used to produce thin angled cone of parts, with reduced forming force and enhanced mechanical and surface quality for a good finished part, compared with other method formed parts. So shear spinning technique is used widely in industrial production. Especially shear spinning and flow forming techniques are used frequently in automotive, aerial, defense industry. In this paper, finite element method analysis of shear spinning for a cone shape workpiece is carried out to study effects of forming depth and lead angle on forming force. The axial and radial forces on several forming depth and lead angle conditions are obtained.
Ultrasonic Inspection Technology of Defect Detection of Propellant/Liner Debond & Propellant Microcrack
Na, Sung-Youb ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 1, 2007, Pages 34~42
Ultrasonic inspection method is more profitable than X-ray radiographic inspection in cost and effect of defect detection such as debond, damage, and it doesn't need special constructions. The method can also be a possible real time inspection with safety. This report explains 1)the experiment and analysis of ultrasonic property of solid propellant, 2)the inspection methods of propellant/liner debond by inside or outside inspection, and 3)the inspection methods of propellant microcrack by damage. From the results, it is possible to detect the defect of propellant/liner debond by inside or outside inspection. Futhermore, it can be possible to detect the propellant microcrack caused by damage using the ultrasonic attenuation.
Defect Diagnostics of Gas Turbine with Altitude Variation Using Hybrid SVM-Artificial Neural Network
Lee, Sang-Myeong ; Choi, Won-Jun ; Roh, Tae-Seong ; Choi, Dong-Whan ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 1, 2007, Pages 43~50
In this study, Hybrid Separate Learning Algorithm(SLA) consisting of Support Vector Machine(SVM) and Artificial Neural Network(ANN) has been used for developing the defect diagnostic algorithm of the aircraft turbo-shaft engine in the off-design range considering altitude variation. Although the number of teaming data and test data highly increases more than 6 times compared with those required for the design condition, the proposed defect diagnostics of gas turbine engine using SLA was verified to give the high defect classification accuracy in the off-design range considering altitude variation.
Recirculation Characteristics by the Inlet Angle and Dome Size of a Liquid Ramjet Combustor using PIV Method
Kim, Gyu-Nam ; Lee, Choong-Won ; Sohn, Chang-Hyun ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 1, 2007, Pages 51~56
Flow characteristics in a liquid fuel ramjet combustor were investigated using the PIV method. The combustor has two rectangular inlets that form a
angle each other. Three cases of test combustors are made in which those inlet angles are
. The experiments were performed in a water tunnel test with the same Reynolds number as Mach 0.3 at the inlet. PIV software was developed to measure the characteristics of the flow field in the combustor. A large and complex recirculating flow was measured in the dome area with 4 different dome size. Experimental results shows that 1/3 dome size of combustor diameter is suitable and smaller inlet angle provide large recirculation flow at the dome of combustor as a frame holder in this experimental ranges but need to consider secondary recirculation flow in a junction region to optimize the configuration of ramjet combustor.
An Experimental Study of the Rocket Preburner Injector
Choi, Seong-Man ; Yang, Joon-Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 1, 2007, Pages 57~63
The oxidizer-rich preburner is applied to the high efficiency closed cycle rocket propulsion system. This system is generally operated on oxidizer-fuel mixture ratio over than 50. The spray quality and mixing performance are very important for stable combustion of this preburner. This paper presents basic design concept and spray characteristic of the oxidizer-rich preburner injector and this result could be applied to the development of the oxidizer rich preburner system.
Cryogenic Performance Test of a Turbopump Inducer
Kim, Jin-Sun ; Kim, Jin-Han ; Hong, Soon-Sam ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 1, 2007, Pages 64~70
A test facility was developed where an inducer for a liquid rocket engine turbopump can be tested using liquid nitrogen as a working fluid. At the facility, a hydrodynamic performance test and a cavitation performance test for an oxidizer turbopump were carried out. Head-flow relation at liquid nitrogen test was similar to the case at water test. However, cavitation performance at the liquid nitrogen was superior to the case at water test, which results from the thermodynamic effect of cavitation.
Review of Combustion Instability in Liquid Propellant Rocket Engines
Khil, Tae-Ock ; Im, Ji-Hyuk ; Yoon, Young-Bin ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 1, 2007, Pages 71~84
The review of the liquid propellant rocket engine is presented. The combustion instabilities which were discovered on solid and liquid propellant rocket engines in 1930, have occurred on propulsion devices, such as gas turbine, ramjet, scramjet and rocket, and thus a study on the combustion instability became necessary. However, this problem has not been solved yet. Therefore, we investigated causes and mechanisms of the combustion instability and surveyed the efforts of solving combustion instability in various countries for developing stable liquid propellant rocket engines.