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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 9, Issue 4 - Dec 2005
Volume 9, Issue 3 - Sep 2005
Volume 9, Issue 2 - Jun 2005
Volume 9, Issue 1 - Mar 2005
Selecting the target year
Catalytic Decomposition of Hydrogen Peroxide for Application on Micro Propulsion
An Sung-Yong ; Lee Jong-Kwang ; Rang Seong-Min ; Kwon Se-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 4, 2005, Pages 1~8
An experimental investigation of a microthruster that uses hydrogen peroxide as a monopropellant is described. The study comprises of preparation method of silver as a catalyst and performance evaluation of a mesoscale reactor. Reduction of silver in
resulted in the best reactivity of all the treatment method tested. A mesoscale reactor was built to find the optimum configuration for full decomposition of propellant. The catalyst bed was made of a glass wafer substrate sputtered with silver and had a length of 20 mm. We measured the conversion rate with varying feed rate of
and preheating temperature. With the feed rate of
, the space time within the reactor varies as well. For the bed length of 20 mm, space time more than 480 s was required for full conversion.
Acoustic-Damping Characteristics of Half-Wave Resonator in a Combustion Chamber of Liquid Rocket Engine
Sohn Chae-Hoon ; Park I-Sun ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 4, 2005, Pages 9~15
A linear acoustic analysis is performed to explore the characteristics of acoustic damping by a gas-liquid scheme coaxial injector in a liquid rocket engine. The injector can play a role of acoustic resonator. Acoustic-damping characteristics of half-wave resonator are compared with those of quarter-wave resonator. Various effects of the boundary absorption coefficient, injector length and sound speed in combustion chamber and resonator are investigated. As a result, short tuning length of resonator and low sound speed of the medium have a favorable effect on acoustic damping. As the boundary absorption coefficient decreases, the tuning range of the resonator length becomes narrower.
The Effects of Forming Depth and Feed Rate on Forming Force of Backward Flow Forming
Nam Kyoung-O ; Yeom Sung-Ho ; Kwon Hyuk-Sun ; Hong Sung-In ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 4, 2005, Pages 16~22
The flow forming has been used to produce long thin walled tube parts, with reduced forming force and enhanced mechanical and surface quality for a good finished part, compared with other method formed parts. So flow forming technique is used widely in industrial production. Especially spinning and flow forming techniques are used frequently in automotive, aerial, defense industry. In this paper, finite element method analysis of three-roller backward flow forming of a workpiece is carried out to study effects of forming depth and feed rate on forming force. The axial and radial forces on several forming depth and feed rate conditions are obtained.
The Aging Effect of
K3B/1M7 Laminates in
Kim Hyung-Won ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 4, 2005, Pages 23~30
The Hygrothermal aging of the laminates of
water was studied as a function of immersion time prior to forming microcracks. The factors causing the
water to degradation of the laminates could be the degradation of the matrix toughness, the change in residual stresses or the interfacial damage between the fiber and the matrix. The times to saturation in
water for the laminates and for the neat resin were 100 hours and 500 hours. After 500 hours aging of the neat resin, the glass transition temperature was changed less than 1% by DSC test, and the weight gain was 1.55% increase with the diffusion coefficient
and the fracture toughness was decreased about 41%. After 100 hours fully saturated aging of the
K3B/IM7 laminates in
water, the weight gain was 0.41% increase with the diffusion coefficient
. In 100 hours, the loss of the fracture toughness of the laminates was 43.8% of the original toughness by the microcracking fracture toughness criterion. Therefore, the main factor to degrade the microcracking toughness of the laminates could be the degradation of the matrix fracture toughness.
A Study on Combustion Characteristics of Hybrid Rocket with the Variation of L/D Ratio
Kim Soo-Jong ; Kim Jin-Kon ; Lee Seung-Chul ; You Woo-Jun ; Lee Jung-Pyo ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 4, 2005, Pages 31~38
In this paper, the combustion characteristics of a hybrid propulsion system were studied with various L/D(length vs diameter) ratio of the single po.1 type solid fuel. Experiments were performed for 2 cases with the fixed grain port diameter and fuel length respectively. For the first case, results show that there are no large variations for regression rates as the L/D ratio changes. And as the L/D ratio increases, the O/F ratio decreases and thrust, characteristic velocity tends to increase. For the second case, there is no large change for O/F ratio, thrust and characteristic velocity as L/D ratio changes. On the other hand, as the L/D ratio decreases, only the regression rate tends to increase. Experimentally, exponent n in
was found about 0.5 and then the O/F ratio was shown nearly constant. In the experiment, PE and gas oxygen were used as a fuel and an oxidizer.
Structural Analysis of Liquid Rocket Thrust Chamber Regenerative Cooling Channel at Room Temperature
Ryu Chul-Sung ; Chung Yong-Hyun ; Choi Hwan-Seok ; Lee Dong-Ju ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 4, 2005, Pages 39~47
The structural analysis and water pressure tests are performed for liquid rocket thrust chamber regenerative cooling channel specimens at room temperature condition. Material properties of copper alloy to be used in the elastic-plastic structural analysis are obtained by uniaxial tension test at room temperature. The plate-type cooling channel specimens are manufactured and performed water pressure test to verify the analysis results. The results of elastic-plastic structural analysis and water pressure test show resonable agreements though with minor differences and it is revealed that structural stability of regenerative cooling channel is highly affected by the manufacturing tolerances due to very thin cross-sectional thickness of the cooling channel.
The Effect on the Film Cooling Performance of Thrust Chamber with Combustion Performance Parameters
Kim Sun-Jin ; Jeong Chung-Yon ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 4, 2005, Pages 48~54
An experimental study was carried out to investigate the effect of film cooling in the lab-scale liquid rocket engine using liquid oxygen(LOx) and Jet A-1(Jet engine fuel) as propellants. Film coolants(Jet A-1 and water) was injected through the film cooling injector. The outside wall temperature of the combustor and film cooled length were determined for chamber pressure, mixture ratio, and the different geometries(injection angle) with the percent film coolant flow rate. The loss of characteristic velocity was determined for the case of film cooling with water and Jet A-1. As chamber pressure increased, the outside wall temperature increased in the nozzle but unchanged over the 9 percent film coolant flow rate for the combustion chamber used in this study. Characteristic velocity wasn't affected with the mixture ratio over the 9 percent film coolant flow rate.
Measurement of the fuel distribution in a scaled ATR combustor using PLIF
Jin Yu-In ; Yang In-Young ; Choi Young-Hwan ; Yang Soo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 4, 2005, Pages 55~65
Mixing performance between fuel and oxidizer is a significant parameter of combustion efficiency and stability in an air-turbo ramjet combustor. Two types of petal mixer were experimented to research the mixing performance. Mixing performance and fuel distribution images were obtained for petal mixers. Planar laser-induced fluorescence(PLIF) was used to obtain 2-D fuel distribution. The obtained images were processed in order to make use of the image information to a quantitative level. The results of analyzing the fluorescence images could be useful to find better mixing performance between mixers.
An Experimental Study on the flow Characteristics of a Supersonic Turbine Cascade as the Leading Edge Shape and the Nozzle-Cascade Cap
Cho Jong-Jae ; Kim Kui-Soon ; Kim Jin-Han ; Jeong Eun-Hwan ; Jeong Ho-Kyung ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 4, 2005, Pages 66~72
In this paper, a small supersonic wind tunnel is designed and built to study the flow characteristics of a supersonic impulse turbine cascade. The flow is visualized by means of a single pass Schlieren system. The supersonic cascade with 2-dimensional supersonic nozzle was tested for various blade leading edge shapes and gaps between the nozzle and cascade. Highly complicated flow patterns including shocks, nozzle-cascade interaction and shock boundary layer interactions are observed.
An Effective Pivot Trace Algorithm for Movable Nozzle using Neural Network
Kim Joung-Keun ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 4, 2005, Pages 73~80
In general, the performance of movable nozzle used for thrust vector control in solid rocket motor is estimated on the basis of the effective pivot of nozzle. However, it is nearly impossible to define the exact effective pivot by the mathematical model or experimental technique owing to pivot dynamics. In this paper, pivot dynamic properties were investigated by ADAMS simulation technique and trajectory of the exact effective pivot was modelled by the artificial neural network. Comparison of the proposed method was made with the virtual movable nozzle (computer simulation) to verify the method, and showed good agreement. Therefore, the proposed method will be applicable to predict the effective pivot of movable nozzle during bench or ground test.
A Study on Compressor Map Identification using Artificial Intelligent Technique and Performance Deck Data
Ki Ja-Young ; Kong Chang-Duck ; Lee Chang-Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 4, 2005, Pages 81~88
In order to estimate the gas turbine engine performance precisely, the component maps containing their own performance characteristics should be needed. In this study a component map generation method which may identify compressor map conversely from a performance deck provided by engine manufacturer using genetic algorithms was newly proposed. As a demonstration example for this study, the PW 206C turbo shaft engine for the tilt rotor type Smart UAV(Unmanned Aerial Vehicle). In order to verify the proposed method, steady-state performance analysis results using the newly generated compressor map was compared with them performed by EEPP(Estimated Engine Performance Program) deck provided by engine manufacturer. And also the performance results using the identified maps were compared with them using the traditional scaling method. When the performance analysis is performed at far away operation conditions from the design point, in case of use of e component map by the traditional scaling method, the error of the performance analysis results is greatly increasing. In the other hand, if in case of use of the compressor map generated by the proposed GAs scheme, the performance analysis results are closely met with those by the performance deck, EEPP.
A Study on Deformation Behavior of Thrust Cut Off System under High Pressure
Park Sung-Han ; Chang Hong-Been ; Lee Hwan-Gyu ; Kang Moon-Jung ; Kim Jae-Hoon ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 4, 2005, Pages 89~95
Thrust cut off(TCO) system is installed at the port of a rocket motor case forward dome. The snap ring and the closure are escaped sequentially by pulling out a wedge under internal pressure. The hydraulic structural tests of TCO and numerical simulations were performed, and both results were compared to understand the deformation behavior of TCO. By increasing splines symmetrically, the sealing capacity of TCO can be improved significantly. The escape pressure of TCO increases according to the increase of friction coefficient and there is a critical friction coefficient beyond which the snap ring can not be nearly escaped even after forced escape of wedge. Under low friction coefficient the snap ring is contracted to radial direction and easily escaped. But, under high friction coefficient, the snap ring can not be escaped from the port even after severe plastic deformation.
PID Control Characteristic of Thrust Control Valve for Liquid-Propellant Rocket Engine
Kim Hui-Tae ; Lee Joong-Youp ; Han Sang-Yeop ; Kim Young-Mog ; Oh Seung-Hyub ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 4, 2005, Pages 96~103
The main purpose of launch vehicle is to insert satellite into a target orbit safely and correctly. To accomplish the main purpose of launch vehicle, the inserting velocity, inserting angle, and final mass of launch vehicle should be within the allowable range. In general, such requirements are satisfied with applying TCS(Thrust Control System) and TDS(Tank Depletion System), which manage thrust and mixture ratio by controlling propellant flow rate with thrust and mixture ratio control valves. In this study, the control characteristics of thrust and mixture ratio control valve were examined by PID control logic for stable operation of liquid-Propellant rocket engine at on-dosing point. The analysis on the control characteristics of control valves was done with AMESim code and the results from control valve test facility at KARI.
Altitude Engine Test
Lee Jin-Kun ; Kim Chun-Taek ; Yang Soo-Seok ; Lee Dae-Sung ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 4, 2005, Pages 104~111
Gas turbine engines for aircraft are usually operated at the altitude condition which is quite different from the ground condition. In order to measure the precise performance data at the altitude condition, the engine should be tested at the altitude condition by a real flight test or an altitude simulation test with an altitude test facility. In this paper, the present state of the altitude test facility and the test technologies at urn(Korea Aerospace Research Institute) will be introduced.
The Tendency in Solid Propellant Technology for Missiles
Yim Yoo-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 4, 2005, Pages 112~120
The solid propellants have been most widely used for the military rockets or missiles all over the world and the efforts have been focused on the enhancement of propellant performance up to 1980s. lately in company with the distinguished development in the intelligence and communication technology, the more accurate guidance as well as maneuverability has been required in the military weapon system. To meet the requirements such as a high maneuverability, insensitiveness, or stealth of missile, the researches have been doing to develop the solid propellants which have a quality of ultra-fast burning rate, insensitiveness, low signature or the like.