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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 1, Issue 2 - Dec 1997
Volume 1, Issue 1 - Jun 1997
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The Structural Integrity Evaluation of Composite Pressure Vessel Using Acoustic Emission
Journal of the Korean Society of Propulsion Engineers, volume 1, issue 2, 1997, Pages 1~11
During hydroproof test of composite pressure vessel, acoustic emission signal was measured and analyzed to evaluate structural integrity of composite motor case. When pressure was held for 1 min. at constant pressure from low pressure level to high pressure level, the pattern of hit rate of good composite pressure vessel is increased with higher value than that of bad composite pressure vessel. This report also presents detection possibility of burst location approximately in the range of 25∼36％ of burst pressure using energy rate. In case that it is difficult to detect burst location of composite motor case, it is possible to detect burst location, i.e. structurally weak location of composite pressure vessel with applying same pressure lower than maximum expected operating pressure(MEOP) repeatedly.
Aerodynamic and Structural Design for Medium Size Horizontal Axis Wind Turbine Rotor Blade with Composite Material
Journal of the Korean Society of Propulsion Engineers, volume 1, issue 2, 1997, Pages 12~21
Nowadays, non-pollution energy sources have been strongly needed because of the exhaustion of fossil fuels and serious environmental problems. Because wind energy can be enormously obtained from natural atmosphere, this type of energy has lots of advantages in a economic and pollution point of view. This study has established the aerodynamic and structural design procedure of the rotor blade with an appropriate aerodynamic performance and structural strength for the 500㎾ medium class wind turbine system. The aerodynamic configuration of the rotor blade was determined by considering the wind condition in the typical local operation region, and based on this configuration aerodynamic performance analysis was performed. The rotor blade has the shell-spar structure based on glass/epoxy composite material and is composed of shank including metal joint parts and blade. Structural design was done by the developed design program in this study and structural analysis, for instance stress analysis, mode analysis and fatigue life estimation, was performed by the finite element method. As a result, a medium scale wind turbine rotor blade with starting characteristics of 4m/s wind speed, rated power of 500㎾ at 12m/s wind speed and over 20 years fatigue life has been designed.
Analysis of Flows in the Combustor with Recirculating Flow Regime
Journal of the Korean Society of Propulsion Engineers, volume 1, issue 2, 1997, Pages 22~31
We developed a general purpose program for the analysis of flows in the combustor with recirculating flow regime and simulated the flows. The program uses non-staggered grids based on finite volume method and the primitive variables are cartesian velocities. The combustion model is irreversible one step reaction with infinite chemistry The Favre averaged governing equations are considered and the clipped gaussian distribution is considered as a probability density function of the conserved scalar. We calculated turbulent diffusion flame with recirculating flow regime. Simulation shows two recirculating regions like experimental results. Velocity, turbulent kinetic energy, temperature and concentration distribution in simulation agree well with experimental data.
Flow Characteristics of Acoustically Excited Axisymmetric Impinging Jet
Journal of the Korean Society of Propulsion Engineers, volume 1, issue 2, 1997, Pages 32~40
The velocity and turbulent intensity of the jet core are affected by the vortices around jet. By the control of vortex acoustically, we can expect the changes of the flow and heat transfer characteristics of free and impinging jets. On this paper, we studied the effects of vortex forcing. If vortex pairings are promoted by acoustic excitation, the turbulent intensity is increased and the high heat transfer coefficients are obtained at the small nozzle to plate distance. On the other hand, it has low turbulent intensity at the center of jet. However due to increase of potential core length, it is more effective at the large nozzle to plate distance. Therefore the excited frequency, especially its subharmonic frequency, has an important role to control the jet flows.
Analytical Study on the Compressure Flow Through a Double Orifice
Journal of the Korean Society of Propulsion Engineers, volume 1, issue 2, 1997, Pages 41~47
The flow choking in a double orifice is expected to depend on cross-sectional area ratios of the orifices, upstream Mach number and total pressure loss between the orifices. However, no research has been reported on the problems of the compressible flow through a double orifice so far. The present study investigated analytically the choke conditions of the compressible gas through a double orifice, using a simple compressible theory. The orifice area ratio, upstream Mach number, and total pressure loss were involved to find the effects that they have on the flow choking. The results of analytical method show that for orifice area ratios below 1.0, flow choking moves from the first to the second orifice as the total pressure loss increases, however, for orifice area ratios over 1.0, it occurs only at the second orifice.
Structural Dynamic Modification of Fixture using Antiresonance Frequency Analysis
Journal of the Korean Society of Propulsion Engineers, volume 1, issue 2, 1997, Pages 48~57
The method of antiresonance frequency analysis of multi-input system is proposed. The structural dynamic modification using antiresonance frequency analysis is also applied to reduce the undertest at specimen attachment points on the fixture in environmental vibration test, which is resulted from the inconsistency of antiresonance frequencies. Several computer simulations show that the proposed method can remove the undertest problem which is not removed in conventional vibration test control. And the effectiveness of the method is verified with the impact hammer excitation of aluminium fixture model.
An Experimental Study on the Regression Rate of the Hybrid Rocket with
/HTPB Propellant Combination
Journal of the Korean Society of Propulsion Engineers, volume 1, issue 2, 1997, Pages 58~66
To investigate the effect of the oxidizer mass flow rate on the fuel regression rate of the hybrid rocket, a laboratory size rocket was designed and ground fire test were carried out. Oxidizer was gaseous oxygen and HTPB was used as a fuel. Following correlation was obtained from the experiment.
Development of Attitude Control Thruster for KOMPSAT
Journal of the Korean Society of Propulsion Engineers, volume 1, issue 2, 1997, Pages 67~73
This paper shows the development status of attitude control thruster for KOMPSAT(Korea Multi-Purpose Satellite). Hanwha Corp. has manufactured and delivered 1.0 lbf monopropellant thrusters under the technology transfer of TRW Co. in U.S.A regarding design, analysis and manufacturing of MRE-1 thruster These thrusters will be installed to KOMPSAT which is scheduled to be launched in July 1999. Monopropellant thrusters can provide reliable and cost-effective means of propulsive control for middle class satellite and maneuvering control systems. Some information concerning with system specification, performance analysis/simulations and manufacturing process has been introduced in this paper.
2-Parameter High Frequency Combustion Instability Model
Journal of the Korean Society of Propulsion Engineers, volume 1, issue 2, 1997, Pages 74~83
The definition of burning admittance and conventional n-
stability rating technique are combined to investigate the high frequency combustion instabilities inside the cylindrical combustion chamber. Perturbed flow variables are written as the sum of fluctuating and time-averaged mean quantities on the assumption that the terms of the order higher than unity are sufficiently small, hence linearized governing equations could be formulated. Chamber admittances up and downstream of the flame front calculated with appropriate boundary conditions result in the burning admittance and corresponding n-
neutral stability curve. Configurational and operational design factors are tested to detect the unstable wave-induced LOX-RP1 combustion instabilities. Operational design factors, e.g. pressure or O/F ratio, appear less influential to drive high frequency instability while the location of the flame front and configurational factors enhance or deteriorate the stabilities strongly. Conclusively, LOX-RP1 combustion inside the cylindrical combustion chamber is apt to be unstable against long residence time and shortened chamber length.
A Steady-State Simulation and Experimental Study of Turboshaft Engine with Free Power Turbine
Journal of the Korean Society of Propulsion Engineers, volume 1, issue 2, 1997, Pages 84~90
The turboshaft engine with the free power turbine has been used for various purposes, for instance electric power generator, emergency power source, helicopter powerplant and so on. Steady-state simulation program was developed and experimental tests was carried out for comparing with computer simulation results. The test unit was composed of 1-stage centrifugal compressor, the can type combustor chamber, 1-stage radial type compressor turbine, and radial type free power turbine, and its output power is obtained from 3-phase AC generator. Main component characteristics which was used for the steady state simulation program, were obtained from the manufacturer of the test unit, and modified from experimental results of test unit. In comparison between computer simulation and experimental test results even though the test unit has the operational limit, deviation of component performance characteristics in simulation were within 6％ range of experimental results.
Evaluation of the Aging Effects on the Performance of the Pyrotechnic Igniter
Journal of the Korean Society of Propulsion Engineers, volume 1, issue 2, 1997, Pages 91~102
In order to evaluate the effects of aging on the ignition performance, pyrotechnic igniters were separated from twelve-year-old, fifteen-year-old, and sixteen-year-old live rocket motors. The characteristic values of the ignition material were measured, and the firing tests of the igniters were performed. The moisture content, the outer dimension, the crush strength, the thermal decomposition characteristics, and the heat of formation the B/
ignition pellet were measured. The crush strength was increased and the heat of formation was reduced as aged, but no change was detected for other characteristic values. The burning test results of the igniter pellet in the closed bomb and the inert motor showed that the burning rate of the ignition pellet was increased by 10%, and the integration of pressure
of the p-t curve was reduced by 15% for aged samples. It was inferred that the burning rate was increased as the crack was appeared in the pellet and
could be proportionally decreased with the heat of explosion.