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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 3, Issue 4 - Dec 1999
Volume 3, Issue 3 - Sep 1999
Volume 3, Issue 2 - Jun 1999
Volume 3, Issue 1 - Mar 1999
Selecting the target year
Performance Analysis of Secondary Gas Injection for a Conical Rocket Nozzle TVC(I)
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 1, 1999, Pages 1~8
In the present paper an attempt has been made to simulate the secondary injection-primary flow interaction in the conical rocket nozzle and to derive the performance of secondary injection thrust vector control(SITVC) system. Complex three-dimensional flowfield induced by the secondary injection is numerically analyzed by solving unsteady three-dimensional Euler equation with Beam and Warming's implicit approximate factorization method. Emphasized in the present study is the effect of secondary injection such as secondary mass flow rates and the momentum of secondary/primary nozzle flow mass rates upon the gross system performance parameters such as thrust ratio, specific impulse ratio and deflection angle. The results obtained in terms of system performance parameters show that lower secondary mass flow rate is advantageous for to reduce secondary specific impulse loss. It is further found that the nozzle with secondary jet injected downstream and interacting with fast primary flow is preferable for efficient and stable SITVC over the wide range of use with the penalty of side specific impulse loss.
Effect of Operating Condition of Airblast Atomizer on Twin spray characteristics and interaction
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 1, 1999, Pages 9~14
The effect of operating condition was studied experimently on the characteristics of twin sprays ejected from two airblast atomizers, within the range of the mass air-fuel ratio 1.36∼3.54. Water and nitrogen gas were used as test fluids for the experiments. Spray characteristics of liquid spray were measured with measurement of mass distribution and instantaneous image of the spray cone. Experimental results show that the maximum specify of the distribution were lowered but distributed over the larger area when the ROA ratio increased, Center of mass position did not change with increasing water mass flow, Increase of the nozzle distance has an small effect on mass distribution of interaction area but distributed over the larger area. It was also conformed that the effect of interaction near central point of collision decreased with the increase of the ROA ratio on interaction area from comparison using superposition method
The Effect of Compressibility Terms on the Simulation of the Flowfield around a Cylinderical Afterbody
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 1, 1999, Pages 15~23
model is used for simulation of flowfield around the cylinderical afterbody. In addition to two-equation turbulence model, modification terms for the compressibility effects are applied to the simulation. Although the estimations of the skin friction and the surface pressure distribution at hypersonic ramp flowfield were satisfactory, the result of the simulation with the modifications for this flowfield is worse than that of the original K-
model. The compressiblility modification terms do negative effects on the estimation. The basic research on the turbulence model for the compressible flowfield has to be further conducted.
Optimal Parameter Selection by Health Monitoring of Gas Turbine Engines using Gas Path Analysis
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 1, 1999, Pages 24~33
For performance prediction and diagnostics of gas turbine engines, linear and non-linear gas path analysis are applied. In order to find optimal instrument parameters to detect the physical faults such as (outing, erosion and corrosion, non-linear gas path analysis is used. A typical industrial gas turbine engine, TB5000, is used to study the effect of physical faults on engine performance. Through comparison of RMS error between linear and non-linear gas path analysis, the optimal instrument parameters can be defined. As a result, it is found that the linear GPA has the level of error introduced by the assumption of the linear mode: can be of the same order of magnitude as the fault being soughtwhile the non-linear GPA can be solved the non-linear relationships between dependent and independent parameters using an iterative method such as the Newton-Raphson method with sufficient accuracy.
Flow and Heat Transfer Characteristics on Oblique Impingement Surface by Single Axisymmetric Jet
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 1, 1999, Pages 34~40
An experimental study has been conducted to determine the effects of inclined impinging jet on the local heat transfer coefficients. A single jet with nozzle diameter of 24.6 mm was tested for Reynolds numbers from 10,000 to 70,000 and nozzle-to-plate spacings of 2~6 jet diameters. The angle of inclination of the impingement surface relative to the horizontal surface was varied from
(normal impingement) to
. The results indicate that the point of maximum heat transfer is moved up from the geometrical stagnation point of inclined surface by Coanda effect. The local heat transfer coefficients on the minor jet region decrease more rapidly than on the major jet region, thus creating an imbalance in the cooling capabilities on the two sides.
Analysis of the Burning Rate of Solid Propellant Accounting for the Evaporation on the Surface
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 1, 1999, Pages 41~47
The burning rate of solid propellant is one of the key parameter associated with the dynamic characteristics of combustion and the combustion performances. In the AP propellants, the evaporation on the reacting surface as well as the decomposition of the propellant is of great importance in determining the overall burning rate. In this study, a theoretical analysis was conducted to obtain the expression for burning rate in the steady state combustion with the energy and species equations in the condensed phase when the radiative heat flux partially contributes to the total heat transfer to the propellant surface.
Preparation of Phase Stabilized Ammonium Nitrate(PSAN) containing Potassium Dinitramide(KDN) by a Salting Out Process
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 1, 1999, Pages 48~54
A method was disclosed for making phase stabilized ammonium nitrate(PSAN), where the process involves precipitation of ammonium nitrate(AN) with potassium dinitramide(KDN) from the aqueous solutions of their salts using a salting out technique. The organic solvent used as a precipitant was acetonitrile. The DSC results showed that the precipitates are PSAN, and AN is stable over the temperature range from
if the KDN concentration in the precipitated solids is greater than about 6 wt.%. The particles prepared are expected to be useful as an oxidizer for the solid rocket propellants and explosives.
A Study on the Generating Piece and Arrangement Method Using the Parametric Macro
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 1, 1999, Pages 55~64
Large size shipyards have peformed the generating of piece and the nesting using shipbuilding-oriented CAD program, which requires higher skilled operators and lots of costs. So, medium and small size shipyards have pursued different types of piece generation and nesting (arrangement method). This research is to develop a program for the generating of pieces with parametric macro method and a STRIP program for the nesting of pieces by PC, which can be applied in such shipyards.
An Experimental Study of Shock Wave Effects on the Model Scramjet Combustor
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 1, 1999, Pages 65~71
An experimental study was carried out in order to investigate the effect of shock waves on the supersonic hydrogen-air jet flames stabilized in the Mach 2.5 model scramjet combustor. This experiment was the first reacting flow experiment interacting with shock waves. Two identical
wedges were mounted on the diverging sidewalls of the combustor in order to produce oblique shock waves that interacted with the flame. Schlieren visualization pictures, wall static pressures, and combustion efficiency at two different air stagnation temperatures were measured and compared to corresponding flames without shock wave-flame interaction. It was observed that shock waves significantly altered the shape of supersonic jet flames, but had different effects on combustion efficiency depending on air temperatures. At the higher air stagnation temperature and higher fuel flow rates, combustion of efficiency showed a better result.
Review on Mono-hydrazine Thruster Development
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 1, 1999, Pages 72~77
The mono-hydrazine thrusters which have been selected for satellite auxilliarly propulsion system since 1960s were koreanized for KOMPSAT attitude control. In this paper, design and manufacturing, test of the mono-hydrazine thruster were briefly reviewed with KOMPSAT attitude control thrusters and the key technology to be developed in the future for various small thrusters of launch vehicle, satellite and guidance missile were proposed.
A Study on the Burning Characteristics of N-5 Propellant Embedded with Metal Wires
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 1, 1999, Pages 78~85
Burning characteristics of solid propellants embedded with four kinds of metal wires(Ag, Cu, Al, Ni-Cr wire) were studied with varying wire diameters(O.10.8 mm) lot N-5 propellant. It was found that the order of the burning rate increment ratio(
) was Ag wire > Cu wire > Al wire> Ni-Cr wire which was the same as the order of the magnitude of thermal diffusivity. The burning rate increment ratio(
) of N-5 propellant was less than that of composite Propellant because of the difference of adiabatic flame temperature and flame structure. When Ag, Cu and Al wire having high thermal diffusivity were embedded in N-5 propellant, the plateau and mesa characteristics of the double base propellant were disappeared, but not disappeared in the case of propellant embedded with Ni-Cr wire due to its poor thermal conductivity.
Measured Effect of Shock Wave on the Stability Limits of Supersonic Hydrogen-Air Flames
Hwanil Huh ;
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 1, 1999, Pages 86~94
Measured shock wave effects were investigated by changing shock strength and position with particular emphasis on the stability limits of hydrogen-air jet flames. For this purpose, a supersonic nonpremixed, jet-like flame was stabilized along the axis of a Mach 2.5 wind tunnel, and wedges were mounted on the sidewall in order to interact oblique shock waves with the flame. This experiment was the first reacting flow experiment interacting with shock waves. Schilieren visualization pictures, wall static pressures, and flame stability limits were measured and compared to corresponding flames without shock-flame interaction. Substantial improvements in the flame stability limits were achieved by properly interacting the shock waves with the flameholding recirculation zone. The reason for the significant improvement in flame stability limits is believed to be the adverse pressure gradient caused by the shock, which can elongate the recirculation zone.
A Study on the Combustion Characteristics of Composite Solid Propellants at Low Pressure using Vacuum Strand Burner
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 1, 1999, Pages 95~103
Low pressure combustion characteristics of the composite solid propellants were studied in terms of the propellant burning rate, ignition processes, and the structure of the extinguished surfaces. Optical Vacuum Strand Burner(OVSB) system was designed and configured for this purpose. Burning rates of the propellants were measured at subatmospheric pressure by developed test method in OVSB. The ignition and combustion phenomena of the studied propellants in the combustion chamber of OVSB were recorded and analyzed with the camera and VCR(30 frames/s). Burning surfaces of the propellants were extinguished by rapid depressurization method and analyzed with Scanning Electron Microscope(SEM).
Improvement of Fatigue Life and Vibrational Characteristics of Composite Material Propeller Shaft of Vehicle
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 1, 1999, Pages 104~117
The Composite materials has been used in the field of high technology industry because of high specific stiffness and high specific strength. Specially, the composite materials has been widely applied to the field of the aircraft and the transportation by the effectiveness of light weight due to low specific weight and reduction of the parts due to bonding, molding and so on. These advantages about the composite have led to study and apply in the transmission shaft for the aircraft and the drive shaft for the automobile. The composite material propeller shaft with the high vibrational stability was designed and analyzed. In order to verify the analysis, two types of experimental test which are the FFT analyzer with impact hammer and the rotational equipment were applied.