Go to the main menu
Skip to content
Go to bottom
REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
> Journal Vol & Issue
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 12, Issue 6 - Dec 2008
Volume 12, Issue 5 - Oct 2008
Volume 12, Issue 4 - Aug 2008
Volume 12, Issue 3 - Jun 2008
Volume 12, Issue 2 - Apr 2008
Volume 12, Issue 1 - Feb 2008
Selecting the target year
Modeling of high energy laser heating and ignition of high explosives
Lee, Kyung-Cheol ; Kim, Ki-Hong ; Yoh, Jai-Ick ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 3, 2008, Pages 1~8
We present a model for simulating high energy laser heating of metal for ignition of energetic materials. The model considers effect of ablation of steel plate with long laser pulses and continuous lasers of several kilowatts and the thermal response of well-characterized high explosives for ignition. Since there is enough time for the thermal wave to propagate into the target and to create a region of hot spot in the high explosives, electron thermal diffusion of ultra-short (femto- and pico-second) lasing is ignored; instead, heat diffusion of absorbed laser energy in the solid target is modeled with thermal decomposition kinetic models of high explosives. Numerically simulated pulsed-laser heating of solid target and thermal explosion of RDX, TATB, and HMX are compared to experimental results. The experimental and numerical results are in good agreement.
Chemical Equilbrium Analysis of the
- class KARI LRE Nozzle Flow
Lee, Dae-Sung ; Kang, Ki-Ha ; Cho, D.R. ; Choi, Jeong-Yeol ; Choi, H.S. ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 3, 2008, Pages 9~15
Nozzle flow analyses of
-class KARI liquid rocket engine for high altitude propulsion are carried out using a chemically frozen and equilibrium flow analysis code developed previously. It is considered that the combined frozen- and shifting- equilibrium analysis is cost-effective regarding the convergence characteristics and modeling uncertainties, though the non-equilibrium analysis is most reliable approach. A dependable performance prediction could be attainable through the present analyses that account for the recombination process and thermal and kinetic energy recovery during the expansion process with viscous effects.
Flow Analyses for the Improvement of Uniform Distribution at LOx Manifold of a
Kim, Hong-Jip ; Kim, Seong-Ku ; Kim, Jong-Kyu ; Han, Yeoung-Min ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 3, 2008, Pages 16~23
Flow analyses have been performed to investigate the uniformity of propellant flow through the oxidizer manifold of a 30 tonf full-scaled combustor. Injectors were simulated as porous medium layers of equivalent pressure drops. The uniformity of oxidizer propellant has been analyzed for various diameters of holes in vertical/horizontal distributors and configurations of oxidizer inlet to propose an improved design solution. It has been proven that the mass flow uniformity were improved by adjusting the holes in vertical/horizontal distributors.
Experimental approach for catalyst bed sizing of liquid propellant thruster
An, Sung-Yong ; Kwon, Se-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 3, 2008, Pages 24~33
A 50 Newton monopropellant thruster being developed for attitude control in a variety of aerospace application systems is described in this paper. A scaled down thruster with platinum on aluminum oxide in the reaction chamber was tested to determine the catalyst capacity. A scaled up thruster which was designed and fabricated using data obtained from a small scale device was evaluated by its decomposition efficiency based on the temperature, the efficiency of characteristic velocity, and the measurement of thrust. The performance of a scaled up thruster was marked by a measured thrust of 42 Newton, 98 % efficiency of the characteristic velocity, a specific impulse of 123 sec at sea level.
An Experimental Study on Acoustic Absorption in a Model Chamber with a Half-Wave Resonator
Sohn, Chae-Hoon ; Park, Ju-Hyun ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 3, 2008, Pages 34~40
Acoustic design parameters of a half-wave resonator are studied experimentally for acoustic stability in a model chamber. According to the standard acoustic-test procedures, acoustic-pressure signals are measured. Quantitative acoustic properties of damping factor and sound absorption coefficient are evaluated and thereby, the acoustic-damping capacity of the resonator is examined. The diameter and the number of a half-wave resonator, its distribution, and the diameter of an enclosure are selected as the design parameters for optimal tuning of the resonator. Aroustic-damping capacity of the resonator increases with its diameter. When the open-area ratio of the resonator exceeds the optimum value, over-damping appears, leading to the decrease in the peak absorption coefficient and the broadening of absorption bandwidth. As the resonator diameter increases, optimum open-area ratio decreases.
The implementation of the firing control system considering a flight sequence control technique
Lee, Seung-Jae ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 3, 2008, Pages 41~48
One of main functions of the firing control system applied to a rocket propulsion test has been to provide electric current for ignition of a solid rocket motor. This paper describes the design and implementation of an enhanced firing control system for ground propulsion test that can also control and verify various types of squib events and flight sequences.
A Study on the Design and Performance Analysis of a Gun-Launched Projectile with Solid fuel Ramjet(SFRJ)
Lee, Sang-Kil ; Kim, Chang-Kee ; Lee, Sang-Seung ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 3, 2008, Pages 49~59
In this study, the design method of a 155 mm Solid Fuel Ramjet projectile is proposed and a flight performance analysis program through mathematical modelling is developed. Through flight performance analysis, ramjet performance during flight, which is comprised of thrust, specific impulse, pressure recovery ratio, location of shock waves, and magnitude of drag, was predicted. The results show that compared to Rocket Assisted Projectile(RAP), the range was increased by 90 %. Furthermore, how variations in nozzle exit area ratio and the intake area cause variations in range was observed. This research on modeling and simulation methodology will provide useful data for future development of solid fuel ramjet projectiles.
A Study on Defect Diagnostics of Gas-Turbine Engine on Off-Design Condition Using Genetic Algorithms
Yong, Min-Chul ; Seo, Dong-Hyuck ; Choi, Dong-Whan ; Roh, Tae-Seong ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 3, 2008, Pages 60~67
In this study, the genetic algorithm has been used for the real-time defect diagnosis on the operation of the aircraft gas-turbine engine. The component elements of the gas-turbine engine for consideration of the performance deterioration consist of the compressor, the gas generation turbine and the power turbine. Compared to the on-design point, the teaming data has been increased 200 times in case off-design conditions for the altitude, the flight mach number and the fuel consumption. Therefore, enormous learning time has been required for the satisfied convergence. The optimal division has been proposed for learning time decrease as well as the high accuracy. As results, the RMS errors of the defect diagnosis using the genetic algorithm have been confirmed under 5 %.
Three-dimensional Detoantion Wave Dynamics in a Circular Tube
Cho, Deok-Rae ; Won, Soo-Hee ; Shin, Jae-Ryul ; Choi, Jeong-Yeol ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 3, 2008, Pages 68~75
The three-dimensional structure of detonation wave propagating in a circular tube was investigated using a parallel computational code developed previously. A series of parametric study for a circular tube of a fixed diameter gave the formation mechanism of the detonation cell structures depending on pre-exponential factor, k. The unsteady results in three-dimension showed the mechanisms of two, three and four cell mode of detonation wave front structures. The detonation cell number was increased but cell width and length were decreased with increased pre-exponential factor k. In the all multi-cell mode, the detonation wave structure and smoked-foil records on the wall are made by the moving of transverse waves. The detonation wave front structures have the regular polygon and windmill shapes periodically.
Moon, Hee-Jang ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 3, 2008, Pages 76~86
The EP(electric propulsion) is unique in that several energy sources can be utilized to produce the electric energy and that high exhaust velocity can be achieved compared to the conventional chemical propulsion. Though a lot of variety of non chemical propulsion are under study, the fact that the EP's specific impulse ranges widely from 200s to 5000s led most research to concentrate on the electric propulsion research. This paper, therefore, is aimed to introduce the up-todate existing EP family such as electrothermal, electrostatic and electromagnetic thrusters where its operating concepts, characteristics and possible variants are presented for future applications.