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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
Editor in Chief :
Volume & Issues
Volume 2, Issue 3 - Dec 1998
Volume 2, Issue 2 - Aug 1998
Volume 2, Issue 1 - Apr 1998
Selecting the target year
Stress Analysis of Composite Rotor Blade with Sandwich Structure for Medium Class HAWT
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 3, 1998, Pages 1~9
The exhaustion of fossil fuels and serious environmental pollution put the concern about non-po llution energy into the world. On the developments of technology, wind energy has been spotlighted as a non-pollution energy in many countries. This study has carried out the aerodynamic and structural design procedure of the lightweight composite rotor blades with an appropriate aerodynamic performance and structural strength for the 500㎾ medium class wind turbine system. The previous design, which is shell-spar structure, is redesigned to shell-spar- sandwich structure for light weight. Large deformation problem from light weight is examined by non-linear analysis. Local buckling occurred under lower stress than failure stress. The buckling analysis is accomplished to confirm the safety of the composite blade. The stress analysis around pin hole joint part at hub is carried out and it is confirmed that the pin hole is not failed. The results show that the resonance of redesigned blade does not happen in operation range.
An Experimental Study on Flow Characteristics of a Supersonic Impinging Jet
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 3, 1998, Pages 10~19
When an under-expanded supersonic jet impinges on an inclined flat surface, a complex flow structure is established due to the intersection between the flat surface and the shock system of the free jet. This study reports on an experimental results of flows due to under-expanded axisymmetric sonic jets impinging on flat plate. Plate inclination from
were investigated by means of detailed measurements of the surface pressure and schlieren photograph and surface flow visualization. The schlieren photograph are consistent with the pressure distribution and the surface flow visualization pictures are clearly related to the pressure distributions. The maximum wall pressure is found to be large on the inclined plate than on the perpendicular plate.
Analysis of Turbulent Flows with Wall Transpiration
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 3, 1998, Pages 20~35
Characteristics of turbulent flow with wall transpiration is analyzed. The wall transpiration includes both of suction and injection and extends their range to 0~160 of absolute magnitude of Re
. Reynolds number based on inlet velocity also covers wide range of 3
. The turbulent flow with wall transpiration induces change of wall boundary layer and rapid change of turbulent field. This, in turn, leads the change of whole flow field. For predicting this complicated flow field properly, newly modified
model is utilized, which is formed by modifying dissipation rate equation. The modified
model of Chien is also adopted for the comparison of model performance. Analysis shows the newly modified
model is successfully able to reflect the characteristics of turbulent flow field with wall transpiration.ion.
Analysis of Normal Shock-Wave Oscillation in a Supersonic Diffuser
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 3, 1998, Pages 36~46
Shock-wave in a supersonic diffuser flow cannot be stable even in the given pressure ratio which remains constant over time, and oscillates around a certain time-mean position. In the present study, oscillation of a normal shock-wave in a supersonic diffuser was analyzed by a small perturbation method. Upstream pressure perturbation was applied to a supersonic diffuser flow with a normal shock-wave. Stability of shock-wave was investigated by considering the diffuser pressure recovery and frequency of the pressure perturbation. The results obtained show that a stable oscillation of weak normal shock-wave is obtainable for the flow with the Mach number over 1.74. The ratio of sound pressures downstream to upstream of the shock wave increases with increase of the Mach number. The present results agree well with other analytical and experimental results.
A Study on the Preparation of new Functionalized Aminosilanes as a Promising Coupling Agent(I)
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 3, 1998, Pages 47~53
Using Michael Reaction, commercially available 3-aminopropyltrimethoxysilane and N-[3-(trimethoxysilyl)propuyl]ethylenediamine were reacted with various Michael acceptors, ethyl acrylate, acrylonitrile, acrylamide, 2-cyanoethyl acrylate, 2-hydroxyethyl acrylate and 3-(trimethoxysilyl)propylmethacrylate, to the new aminosilanes. All compounds which are [3-(N-2-carboethoxyethyl)aminopropyl]triethoxysilane, [3-(N-2-cyanoethyl)aminopropyl]triethoxysilane, [3-(N-di-2-car-boethoxyethyl)aminopropyl]triethoxysilane, [3-N-di-cyanoethyl) aminopropyl]triethoxysilane, [3-(N-2-cyanoethoxypropionyl)aminopropyl]triethoxysilane, [3-(N-di-2-cyanoethoxypropionyl)aminopropyl]triethoxysilane, [3-(N-di-2-hydroxyethoxy propionyl)aminopropyl]triethoxysilane, [3-(N-2-amidoethyl)aminopropyl]triethoxysil-ane,｛3-[N-(N-di-2-cyanoethyl)ethyl]aminopropyl｝triethoxysilane and ｛3-[N-(3-trimethoxysilylpropyl)-2-methylpropionyl]aminopropyl｝triethoxysilane were succes-sfully prepared in 35-70% yields and which were identified with
-NMR and FT-IR spectroscopy.
A Numerical Simulation of Regenerative Cooling Heat Transfer Processes for the Liquid Propellant Rocket Engine
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 3, 1998, Pages 54~61
A numerical simulation is attempted for the regenerative cooling heat transfer processes of the liquid propellant rocket engine. The heat transfer from the combustion gases to the thrust chamber wall is called gas side heat transfer. This heat is conducted radially to the coolant through the carbon deposit and metallic wall of thrust chamber Finally, this heat is convected away by the coolant flowing along the passages in the thrust chamber. The equivalence of these three heat fluxes of the above processes is utilized to determine the coolant side wall temperature, gas side wall temperature and the heat flux. When the number and shape(width, height) of coolant passages, the shape(size) of thrust chamber, oxidant and fuel properties, coolant properties, oxidant/fuel mixture ratio, coolant inlet temperature, the thickness of carbon deposit formed along the thrust chamber wall during combustion are given, reasonable radial direction temperature distributions and heat fluxes along the thrust chamber axis are obtained.
Effect of Polycaprolactone on the Mechanical Properties of PEG/HMX Propellant
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 3, 1998, Pages 62~69
Mechanical properties of polyethyleneglycol(PEG)/cyclo-tetramethylene tetranitramine(HMX) propellant were studied by adding polycaprolactone(PCP) and silane derivatives as coupling agent. Mechanical properties of the propellant were enhanced by increasing the content of PCP which was partially replaced with PEG. PCP/HMX propellant showed 17% increase in maximum tensile strength and 59% increase in elongation compared to those of PEG/HMX propellant. However, as the content of PCP was increased, the hydrolytic stability of this propellant was found to be deteriorated due to the ester group of PCP by measuring hardness drop of cured propellant and swell ratio difference of PEG/PCP binder stored at
and 90% relative humidity. Hardness of the PEG/PCP/HMX propellant was decreased with increasing triethoxysilyl propionitrile(TESPN) and dinitrosalicylic acid (DNSA) content from accelerated aging at
A Study on the PEG and PCP Binder for Propellant
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 3, 1998, Pages 70~79
The PEG and PCP have been used as a binder of high energy and minimum smoke propellant. In this study, PEG, PCP 0260, PCP 1270 and mixed PEG/PCP as a prepolymer were used, and also used BTTN/DEGDN and BTTN/TMETN as a plasticizer. Before being cured, the solution viscosity of prepolymer and plasticizer was measured with various contents of PCP in PEG and contents of plasticizer at
. The results were shown the increased concentration of PCP enhanced the viscosity of solution due to the hydrogen bond of PCP, and the increased contents of plasticizer undoubtedly decrease the viscosity of solution. The cured binders were tested for mechanical properties and measured for glass transition temperature with various concentration of PCP in PEG and contents of plasticizer. The increased concentration of PCP has shown better mechanical properties. This results were attributed to the H-bond. Also, the glass transition temperature was lowered with the higher contents of PCP Finally, with the higher content of PCP in PEG, the better mechanical properties and the lower glass transition temperature and the higher viscosity of solution were shown.
Development of Propulsion Subsystem for KOMPSAST
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 3, 1998, Pages 80~89
Propulsion subsystem transfers KOMPSAT into mission orbit and controls its attitude. Design factor consists of structure safety, electrical circuit design, consumable power estimation of thermal hardwares, damping device design of fuel transient pressure, and system configuration design by considering plume effect from thruster firing. System level analysis should be performed for verification of system design under launch vehicle and orbital environment. Electrical functional test of thermal control hardware, proof pressure test, cleanliness verification test, and internal/external leakage test of fuel feeding system should be carried out for performance estimation of propulsion system. Design and assembly process of propulsion subsystem was depicted and reliability of system was verified by test analysis in this paper.
Vaporization Characteristics of Liquid Oxygen at High-Pressure Environment
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 3, 1998, Pages 90~98
The vaporization process of liquid oxygen(LOX) at high pressure environment is numerically investigated. The present vaporization model can account for the high-pressure effects such as ambient gas solubility, real gas behavior and variable properties. The predicted phase-equilibrium compositions for
/He system are well agreed with experimental data. The LOX vaporization characteristics is parametrically studied for wide range of the operating conditions encountered in the high-pressure combustion process of liquid rocket engine
A LQR Controller Design for Performance Optimization of Medium Scale Commercial Aircraft Turbofan Engine (II)
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 3, 1998, Pages 99~106
The performance of the turbofan engine, a medium scale civil aircraft which has been developing in Rep. of Korea, was analyzed and the control scheme for optimization the performance was studied. The dynamic and real-time linear simulation was performed in the previous study The result was that the fuel scedule of the step increase overshoot the limit temperature(3105
) of the high pressure turbine and got small surge margine of the high pressure compressor. Therefore a control scheme such as the LQR(Linear Quadratic Regulator) was applied to optimizing the performance in this studies. The linear model was expected for designing controller and the real time linear model was developed to be closed to nonlinear simulation results. The system matrices were derived from sampling operating points in the scheduled range and then the least square method was applied to the interpolation between these sampling points, where each element of matrices was a function of the rotor speed. The control variables were the fuel flow and the low pressure compressor bleed air. The controlled linear model eliminated the inlet temperature overshoot of the high pressure turbine and obtained maximum surge margins within 0.55. The SFC was stabilized in the range of 0.355 to 0.43.
A study on the manufacturing of motor case assembly for K-PSAM propulsion system by Trans. power molding(TPM) process
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 3, 1998, Pages 107~115
This paper deals with the study on injection with EPDM(Ethylene propylene dien ter polymer) the gap which narrow, long, and tubular between an ablative composite tube and a steel motor case. Small size motor assembly was designed and manufactured for man-portable air defense propulsion system. Motor assembly is consisted with steel tube, ablative composite tube and insulation rubber. Ablative composite tube was made of carbon/phenolic prepreg by rolling process and insulation rubber was made of EPDM by TPM(Trans-power molding) process. To select the insulation rubber material, we tested ablative insulation property and degradation property at first and we tested fluidity, adhesive property and hardness of EPDM rubber. Finally we designed TPM process to manufacture motor case assembly and the motor case assembly was examined by non-destructive test(X-ray).