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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 20, Issue 4 - Aug 2016
Volume 20, Issue 3 - Jun 2016
Volume 20, Issue 2 - Apr 2016
Volume 20, Issue 1 - Feb 2016
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A Numerical Study on Cooling Characteristics of a Rocket-engine-based Incinerator Devised for High Burning Rate of Solid Particles
Son, Jinwoo ; Sohn, Chae Hoon ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 2, 2016, Pages 1~10
DOI : 10.6108/KSPE.2016.20.2.001
Cooling characteristics are investigated numerically in the chamber for high-performance burnout of wastes with solid phase. Before the combustion chamber is manufactured, combustion analysis is performed for evaluation of burning rate and cooling performance. A water cooling method is applied and its feasibility for cooling is examined depending on coolant flow rate. Another method of complex cooling is adopted by combining air film cooling with water cooling, leading to improved cooling performance.
Fatigue Crack Growth Behavior of Powder Metallurgical Nickel-based Superalloy using DCPD Method at Elevated Temperature
Na, Seonghyeon ; Oh, Kwangkeun ; Kim, Hongkyu ; Kim, Donghoon ; Kim, Jaehoon ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 2, 2016, Pages 11~17
DOI : 10.6108/KSPE.2016.20.2.011
Powder metallurgy nickel based superalloy has been used in a high temperature part of turbine engine for airplane. The fatigue crack growth behavior was investigated using CT specimens for the materials at room temperature(R.T.),
. The direct current potential drop(DCPD) method suggested by ASTM E647 was used to measure the crack length during fatigue crack growth at various stress ratios. The fatigue crack growth rate at R
Surface Modification of High Energetic Materials by Molecular Self-assembly
Kim, Ja-Young ; Jeong, WonBok ; Shin, Chae-Ho ; Kim, Jin-Seok ; Lee, Keundeuk ; Lee, Kibong ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 2, 2016, Pages 18~23
DOI : 10.6108/KSPE.2016.20.2.018
Self-assembly of organic molecules is formed spontaneously on surfaces by electrostatic interaction with substrate. This research has shown that the self-assembly improves safety and handling tractability of high-energetic materials (HEMs). According to the recent study, control of the specific crystal size for reducing the internal defects is mightily important, because the internal defects are a factor in unstability of HEMs. In turn, we performed self-assembly of organic molecules and HEMs by using nano-sized HEMs, which were produced by drowing-out or milling/crystallization. Surface modification efficiency was decided by size distribution, zeta-potential, friction sensitivity and electrostatic charge.
Experimental Study of the Effect of Side Plate on the Coanda Effect of Sonic Jet
Park, Sanghoon ; Chang, Hongbeen ; Lee, Yeol ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 2, 2016, Pages 24~30
DOI : 10.6108/KSPE.2016.20.2.024
An experimental study for the characteristics of the thrust-vectoring of a sonic jet utilizing the coanda flap installed at a rectangular nozzle exit is performed. Two side plates are installed at both sides of the flap to decrease the three dimensional effects of the jet on the flap surface. Schlieren flow visualizations and quantitative measurements of the deflection angle of thrusting vector show that the side plates are able to delay the separation of the jet at the downstream of the flap surface. Substantial increase in the deflection angle of the jet as high as
and small thrust loss as low as 7% are obtained by the present thrust-vectoring technique using the side plates.
The Study on the Synthesis of Triazole Derivatives as Energetic Plasticizer
Lee, Woonghee ; Kim, Minjun ; Park, Youngchul ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 2, 2016, Pages 31~38
DOI : 10.6108/KSPE.2016.20.2.031
Most of propellants that is used widely in the world release toxic gases such as methane gas and carbon dioxide during combustion which are noxious to the environment. This study established a synthetic process of a high nitrogen containing derivative of triazole, 4,5-bis(azidomethyl)-methyl-1,2,3-triazole (DAMTR), which can be applied as energetic plasticizer to environmental concerns. Also, the compound was characterized by NMR, IR spectroscopy, and physical properties such as glass transition temperature, melting point, decomposition temperature, density, impact sensitivity, viscosity and volatility were measured. In addition, the heats of formation (
) and detonation properties (pressure and velocity) of DAMTR were calculated using Gaussian 09 and EXPLO5 programs.
Disintegration Mechanism of a Coaxial Porous Injector
Lee, Keonwoong ; Kim, Dohun ; Son, Min ; Koo, Jaye ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 2, 2016, Pages 39~45
DOI : 10.6108/KSPE.2016.20.2.039
In a coaxial porous injector, a gas propellant is injected through the porous cylinder surface to the liquid jet which is encircled by a porous cylinder. In this study, to observe the differences in disintegration mechanisms between a shear coaxial injector and a coaxial porous injector, cold-flow tests and 2-D axisymmetric numerical analysis have been carried out. The shadowgraph images and Sauter mean diameters were compared in similar experimental conditions, and the effects of velocity distributions at the inner injector region on the disintegration of liquid jet were investigated through the numerical calculations. As a result, in high air mass flow rate condition, the disintegration performance of coaxial porous injector is better than shear coaxial injector, in spite of a lower velocity at the inner injector region.
An Extraction of Detailed Isoconversional Kinetic Scheme of Energetic Materials using Isothermal DSC
Kim, Yoocheon ; Park, Jungsu ; Kwon, Kuktae ; Yoh, Jai-ick ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 2, 2016, Pages 46~55
DOI : 10.6108/KSPE.2016.20.2.046
The kinetic analysis of a heavily aluminized cyclotrimethylene-trinitramine(RDX) is conducted using differential scanning calorimetry(DSC), and the Friedman isoconversional method is applied to the DSC experimental data. The pre-exponential factor and activation energy are extracted as a function of the product mass fraction. The extracted kinetic scheme does not assume multiple chemical steps to describe the complex response of energetic materials; instead, a set of multiple Arrhenius factors is constructed based on the local progress of the exothermic reaction. The resulting reaction kinetic scheme is applied to two thermal decomposition tests for validating the reactive flow response of a heavily aluminized RDX. The results support applicability of the present model to practical thermal explosion systems.
Sensor Fault-tolerant Controller Design on Gas Turbine Engine using Multiple Engine Models
Kim, Jung Hoe ; Lee, Sang Jeong ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 2, 2016, Pages 56~66
DOI : 10.6108/KSPE.2016.20.2.056
Robustness is essential for model based FDI (Fault Detection and Isolation) and it is inevitable to have modeling errors and sensor signal noises during the process of FDI. This study suggests an improved method by applying NARX (Nonlinear Auto Regressive eXogenous) model and Kalman estimator in order to cope with problems caused by linear model errors and sensor signal noises in the process of fault diagnoses. Fault decision is made by the probability of the trend of gradually accumulated errors applying Fuzzy logic, which are robust to instantaneous sensor signal noises. Reliability of fault diagnosis is verified under various fault simulations.
Study of Separation Mechanism According to the Constraint Condition of Explosive Bolts
Jeong, Donghee ; Lee, Youngwoo ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 2, 2016, Pages 67~74
DOI : 10.6108/KSPE.2016.20.2.067
Explosive bolt is one of separation device that uses high explosive charge, and is separated by pressure formed by an explosion and the resulting shock waves. Explosive bolt having such a mechanism would have to be designed to minimize shock and debris formation generated during separation. In this study, separation tests were carried out with distance as variable for restraining the explosive bolt (Air Gap). Bolt release and its separating shape with variation of air gap is observed, and we used accelerometer to measure the shock wave transmitted through a bound object. In addition, separation behavior of explosive bolt is analyzed using ANSYS AUOTODYN program. By comparing the results of previously performed experiments and analysis, we could confirm the effects of air gap to the release behavior of explosive bolt, and decide optimum constraining environment for specific separation bolts.
A Study on Shock-induced Detonation in Gap Test
Kim, Bohoon ; Kang, Wonkyu ; Jang, Seung-gyo ; Park, Jungsu ; Yoh, Jai-ick ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 2, 2016, Pages 75~85
DOI : 10.6108/KSPE.2016.20.2.075
A pyrotechnic system consisting of donor/acceptor pair separated by a gap relies on shock attenuation characteristics of the gap material and shock sensitivity of the donor and acceptor charges. Despite of its common use, numerical study of such pyrotechnic train configuration is seldom reported because proper modeling of the full process requires precise capturing of the shock wave attenuation in the gap prior to triggering a full detonation of high explosive and accurate description of the high strain rate dynamics of the explosively loaded inert confinements. We apply a Eulerian level-set based multimaterial hydrocode with reactive flow models for pentolite donor and heavily aluminized RDX as acceptor charge. The complex shock interaction, critical gap thickness, acoustic impedance, and go/no-go characteristics of the gap test are quantitatively investigated.
Performance Test of a 75-tonf Rocket Engine Turbopump
Jeong, Eunhwan ; Kwak, Hyun-Duck ; Kim, Dae-Jin ; Kim, Jin-Sun ; Noh, Jun-Gu ; Park, Min-Ju ; Park, Pyun-Goo ; Bae, Jun-Hwan ; Shin, Ju-Hyun ; Wang, Seong-Won ; Yoon, Suck-Hwan ; Lee, Hanggi ; Jeon, Seong-Min ; Choi, Chang-Ho ; Hong, Soon-Sam ; Kim, Seong-Lyong ; Kim, Seung-Han ; Woo, Seong-Phil ; Han, Yeong-Min ; Kim, Jinhan ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 2, 2016, Pages 86~93
DOI : 10.6108/KSPE.2016.20.2.086
Performance tests of a 75-tonf liquid rocket engine turbopump were conducted. The performance of sub-components - two pumps and a turbine - and their power matching were measured and examined firstly near the design speed under the LN2 and kerosene environment. In the real propellant - LOX and kerosene - environment tests, design and off-design performance of turbopump were fully verified in regime of the rocket engine operation. During the off-design performance tests, turbopump running time was set longer than the engine operating time to verify the pump operability and set the pump inlet pressure close to design NPSHr to investigate pump suction capability in parallel. It has been found that developed-turbopump satisfied all of the engine required performances.
Aerodynamic Effect on the Flow Field under the Wing with Varying Aspect Ratio
Cho, Cheolyoung ; Park, Jongho ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 2, 2016, Pages 94~101
DOI : 10.6108/KSPE.2016.20.2.094
In this paper, aerodynamic effects on the flow field under the wing with varying aspect ratio were investigated by measuring pressures on the lower surface of wing and analysing velocity components using Particle Image Velocimetry at Reynolds numbers of
. In case of aspect ratio 4.8 which keeps the wing tip at a distance of 80% chord length from the pylon, the vortex from the wing tip influenced the flow field under the wing by reducing static pressures on the lower surface and increasing the velocity in proximity of the wing tip. Throughout the results, it is observed that aerodynamic effects of wing tip on the flow field around pylon under wing become insignificant as the aspect ratio increases.