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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 10, Issue 4 - Dec 2006
Volume 10, Issue 3 - Sep 2006
Volume 10, Issue 2 - Jun 2006
Volume 10, Issue 1 - Mar 2006
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Numerical Requirements for the Simulation of Detonation Cell Structures
Choi Jeong-Yeol ; Cho Deok-Rae ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 2, 2006, Pages 1~14
Present study examines the numerical issues of cell structure simulation for various regimes of detonation phenomena ranging from weakly unstable to highly unstable detonations. Inviscid fluid dynamics equations with
formulation and one-step Arrhenius reaction model are solved by a MUSCL-type TVD scheme and 4th order accurate Runge-Kutta time integration scheme. A series of numerical studies are carried out for the different regimes of the detonation phenomena to investigate the computational requirements for the simulation of the detonation wave cell structure by varying the reaction constants and grid resolutions. The computational results are investigated by comparing the solution of steady ZND structure to draw out the minimum grid resolutions and the size of the computational domain for the capturing cell structures of the different regimes of the detonation phenomena.
A Study on Performance Diagnostic of Smart UAV Gas Turbine Engine using Neural Network
Kong Chang-Duk ; Ki Ja-Young ; Lee Chang-Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 2, 2006, Pages 15~22
An intelligent performance diagnostic program using the Neural Network was proposed for PW206C turboshaft engine. It was selected as a power plant for the tilt rotor type Smart UAV(Unmanned Aerial Vehicle) which is being developed by KARI (Korea Aerospace Research Institute). For teeming the NN(Neural Network), a BPN(Back Propagation Network) with one hidden, one input and one output layer was used. The input layer has seven neurons: variations of measurement parameters such as SHP, MF, P2, T2, P4, T4 and T5, and the output layer uses 6 neurons: degradation ratios of flow capacities and efficiencies for compressor, compressor turbine and power turbine, respectively, Database for network teaming and test was constructed using a gas turbine performance simulation program. From application of the learned networks to diagnostics of the PW206C turboshaft engine, it was confirmed that the proposed diagnostics algorithm could detect well the single fault types such as compressor fouling and compressor turbine erosion.
Development of a Design Theory of a Pressure Vessel with Combined Structure of the Metal and the Composite
Lee Bang-Eop ; Kim Won-Hoon ; Koo Song-Hoe ; Son Young-Il ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 2, 2006, Pages 23~30
A thery was developed to design a high pressure vessel with combined structure of the metal and the composite to withstand the pressure of several tens of thousands psias to reduce the weight of the impulse motor which produces high level of thrust within several tens of seconds. The elastic-plastic stress analyses were carried out to prove the validity of the design theory. A combustion chamber of the impulse motor was designed by the design theory, fabricated, and tested by the hydraulic pressure and the static firings. The bursting pressures from the tests were compared to those predicted by the design theory and the stress analyses and found to be almost the same. It will be possible to design the high pressure vessel with combined structure of the metal and the composite very easily by the proposed design theory.
A Study on Thermal Characteristics of Stratospheric Airship Considering Radiation Heat Transfer
Kim Seung-Min ; Lee Sang-Myeong ; Park Hwi-Seob ; Roh Tae-Seong ; Choi Dong-Hwan ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 2, 2006, Pages 31~38
A study of thermal characteristics of the airship considering radiation heat transfer has been conducted by building a numerical model for the airship in order to identify the possibility to obtain the reliable flight performance in severe stratospheric heat conditions. The variations of distributed temperature of the skin and the inner flow by free convection have been calculated according to the change of the solar position. As the results of the analyses, the stratospheric heat conditions slightly have an influence on the flight performance of the airship.
Air Similarity Performance Test of Turbopump Turbine
Lim Byeung-Jun ; Hong Chang-Uk ; Kim Jin-Han ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 2, 2006, Pages 39~45
In liquid rocket engine turbopump, it is difficult to evaluate turbine performance for high pressure, high temperature circumstance. Turbine test is often done by using air at similarity condition so that the turbine can be tested at lower risk. This paper describes an air similarity test program of liquid rocket engine turbopump turbine. A test facility has been built to evaluate aerodynamic performance of turbines. The test facility consists of high pressure air supply system, mass flow rate measuring nozzle, test section, hydraulic break, exit orifice for pressure control, instrumentation and control system. This paper also presents how to decide the similarity conditions of the turbine test and describes how to control test conditions. Relative standard deviation of measurement parameter was less than 1% and measured turbine efficiency corresponded with analysis result within 2%.
Performance Study of Supersonic Nozzle with Asymmetric Entrance Shape
Lee Ji-Hyung ; Kim Joug-Keun ; Lee Do-Hyung ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 2, 2006, Pages 46~52
Techniques used for thrust vector control in rocket motors are mainly classified nozzles installed mechanical interference on the expansive region of nozzle(such as jet tabs and jet vanes) and movable nozzles(such as ball&socket and flexible seal). Using the numerical analysis and cold-flow test, this paper evaluates the performance of supersonic nozzle with asymmetric entrance shape when the test nozzle, especially ball&socket, is tilted. Numerical result shows that the effect of the asymmetric entrance shape on the flow field is suddenly diminished at the nozzle throat and downstream is mostly free from the effect of asymmetric entrance shape. Although the calculated thrust and lateral force are less than those of cold-flow test, two results show a fairly good agreement. But the cold-flow test results indicate the effective angles calculated from measured forces are not agreement with the geometric angles.
Axisymmetric Thermal Analysis of 3D Regenerative Cooling System
Kim Sung-In ; Park Seung-O ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 2, 2006, Pages 53~61
Axisymmetric numerical thermal analysis for a 3-dimensional regenerative cooling system in a rocket engine is carried out. To predict the accurate heat transfer with the stiff temperature distribution, several tests have been conducted for the grid size, the properties variation of the coolant and the combustion gas depending on temperature. The axisymmetric heat flux model is defined using fin efficiencies and is designed to be equivalent to the heat flux of the 3-dimensional coolant channel. For comparison purpose, the 1-dimensional analysis using Bartz equation is also conducted. The performance of the present model in predicting the cooling characteristics of a 3-dimensional regenerative cooling system is compared with the 3-dimensional results of RTE(Rocket Thermal Evaluation). It is found that the present method predicts much closer results to those of RTE code than 1-dimensional analysis.
The Wave Propagation in Transversely Isotropic Composite Laminates
Kim Hyung-Won ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 2, 2006, Pages 62~69
In transversely isotropic composite laminates, the velocities, the particle directions and the amplitudes of reflected and transmitted waves were obtained using the equation of motion, the constitutive equation, and the displacement equation expressed by wave number and frequency. Eigenvalue problem involving a velocity was solved by Snell's law. Finally, the results were confirmed by 7300 Carbon fiber/5208 Epoxy materials. This approach could be applied to the detection of flaws in transversely isotropic composite laminates by the water immersion C-scan procedure.
Liquid film Thickness Measurement for a Swirl Injector
Kim Sung-Hyuk ; Kim Dong-Jun ; Yoon Young-Bin ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 2, 2006, Pages 70~77
A specially designed in;ector using electric conductivity was used to measure the liquid film thickness exactly, The measurement conducted through the precise calibration, accuracy is demonstrated in comparison with the previous theory and the results using other measurement method. The variation of internal flow and stability are examined through the variation of liquid film thickness by the time. The tendency of liquid film thickness for geometric parameters was examined by the precise measurement.
Experimental Investigation of Turbopump Turbine : Turbine Performance and Effect of Nozzle-Rotor Clearance
Jeong Eun-Hwan ; Kang Sang-Hun ; Shin Dong-Yoon ; Park Pyu-Goo ; Kim Jin-Han ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 2, 2006, Pages 78~86
This paper presents the performance test result of the 30-ton class turbopump turbine. Test has been conducted using high pressure cold air, The turbine overall performance has been measured for various pressure ratio and rotational speed settings. The nozzle-rotor clearance effect on turbine performance also has been tested for the four kinds of the nozzle-rotor clearance values. We found that turbine efficiency rated 51.1% at its design velocity ratio and pressure ratio of 13.5. We also found that turbine efficiency can be increased by 3.5% for approximately 1mm decrement of the nozzle-rotor clearance from its nominal value.
Measurement of Two-Dimensional Skin Friction Distribution Using the Overall Fringe Images
Lee Han-Sang ; Lee Yeol ; Yoon Woong-Sup ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 2, 2006, Pages 87~94
An experimental research program providing knowledge to measure two-dimensional skin friction variation over a certain region of model surface is presented. In the oil-fringe imaging skin friction(FISF) technique, local slope of a thin oil applied on a test surface is measured from the interference fringe patterns on the oil surface, and its information is then related to the applied shear over the oil by the thin-oil lubrication theory. The FISF technique has been applied for a separation flowfield ahead of a circular cylinder vertically mounted on a flat plate, and it has been found that the FISF skin friction results show good comparison with the other numerical/experimental data obtained for similar conditions. implying an applicability of the technique
A Study on the Design and Modeling of PWM Fuel Metering Unit for Miniature Turbo Engines
Joo Sang-Hyun ; Choi Ho-Jin ; Park Jong-Seung ; Lim Jin-Shik ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 2, 2006, Pages 95~101
A fuel metering unit using PWM(Pulse Width Modulated) solenoid valve has some advantages such as low cost, small size and simple structure. The mathematical model and its experimental rig of the fuel metering unit using PWM solenoid valve and CPDV(Constant Pressure Drop Valve) for miniature turbo engines were constructed. As the results of simulation, some major parameters which have dominant effects on the performance were found. And the experimental results verified the validity of established model by showing the good agreement with the numerical simulation results. Hence, this system modeling could be used effectively in the actual development of a PWM fuel control system.
Defect Diagnostics of Gas Turbine Engine Using Support Vector Machine and Artificial Neural Network
Park Jun-Cheol ; Roh Tae-Seong ; Choi Dong-Whan ; Lee Chang-Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 2, 2006, Pages 102~109
In this Paper, Support Vector Machine(SVM) and Artificial Neural Network(ANN) are used for developing the defect diagnostic algorithm of the aircraft turbo-shaft engine. The system that uses the ANN falls in a local minima when it learns many nonlinear data, and its classification accuracy ratio becomes low. To make up for this risk, the Separate Learning Algorithm(SLA) of ANN has been proposed by using SVM. This is the method that ANN learns selectively after discriminating the defect position by SVM, then more improved performance estimation can be obtained than using ANN only. The proposed SLA can make the higher classification accuracy by decreasing the nonlinearity of the massive data during the training procedure.
Improvement of Bonding Process and Bond Strength of HTPB Propellant/Liner using a Polymeric Curative
Jeong Byung-Hun ; Seo Tae-Seok ; Hong Myung-Pyo ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 2, 2006, Pages 110~114
The study has been performed on the improvement of bonding process and bond strength of HTPB propellant and liner using a polymeric curative. In case of liner using polymeric curative prepared from reaction of HTPB and TDI, migration of curative was decreased at bond interface. So EPDM insulation sanding and Desmodur RE coating process could be omitted in motor case preparation and bond strengths between the HTPB propellant and liner were increased. Also deterioration phenomena of bond strength could not be observed in accelerated aging test.
Technical Review and Analysis of Ramjet/Scramjet Technology II. Scramjet and Combined Cycle Engine
Sung Hong-Gye ; Yoon Hyun-Gull ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 2, 2006, Pages 115~128
A technical analysis of current scramjet and combined-cycle engine is presented. Substantial research has been pursued to characterize the operation mechanism of scramjet propulsion, especially in the areas of flame stabilization and system integration, dramatically over the years in support of both military and space access application. Major technology that had significant impact on the maturation of scramjet propulsion technology are dual combustion ramjet, dual mode ramjet, and combined cycle engine to cover a typical wide rage of flight, up to flight Mach number 10. Notable are the fundamental and practical techniques, for instance, scram propulsion itself, thermal relaxation and protection using endothermic fuel and/or CSiC composit materials, and design/manufacture of movable intake and nozzle, to realize high speed propulsion system in near future.