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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 15, Issue 6 - Dec 2011
Volume 15, Issue 5 - Oct 2011
Volume 15, Issue 4 - Aug 2011
Volume 15, Issue 3 - Jun 2011
Volume 15, Issue 2 - Apr 2011
Volume 15, Issue 1 - Feb 2011
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Study on Fault Diagnostics of a Turboprop Engine Using Fuzzy Logic and BBNN
Kong, Chang-Duk ; Lim, Se-Myung ; Kim, Keon-Woo ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 2, 2011, Pages 1~7
The UAV(Unmanned Aerial Vehicle) which is remotely operating with long endurance in high altitude must have a very reliable propulsion system. The precise fault diagnostic system of the turboprop engine as a propulsion system of this type UAV can promote reliability and availability. This work proposes a diagnostic method which can identify the faulted components from engine measuring parameter changes using Fuzzy Logic and quantify its faults from the identified fault pattern using Neural Network Algorithms. It is found by evaluation examples that the proposed diagnostic method can detect well not only single type faults but also multiple type faults.
Investigation of Combustion Characteristics of Hybrid Rocket with Tapered Grain Port
Kim, Jae-Woo ; Kim, Soo-Jong ; Oh, Jung-Soo ; Do, Gyu-Sung ; So, Jung-Soo ; Moon, Hee-Jang ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 2, 2011, Pages 8~14
In this paper, the combustion characteristics of hybrid rocket fuel with tapered grain port were investigated experimentally. The charging efficiency of convergent and divergent port shape fuel with
taper angle was 6.8% higher than that of cylindrical port shape fuel. The regression rate was increased about 17.5% by using the convergent port shape fuel. On the other hand, in case of divergent port shape fuel, no notable difference of regression rate was observed when compared to that of the cylindrical port shape fuel. In the case of convergent port shape fuel, characteristic velocity and its efficiency were notably increased with respect to cylindrical port fuel. It was found that convergent port shape of hybrid rocket fuel can lead to a better option compared to the conventional cylindrical port in terms of combustion efficiency and performance improvement.
Starting Characteristics Study of Scramjet Engine Test Facility(SETF)
Lee, Yang-Ji ; Kang, Sang-Hun ; Oh, Joong-Hwan ; Yang, Soo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 2, 2011, Pages 15~22
Unlike most aerodynamic wind-tunnel, Scramjet Engine Test Facility(SETF) of Korea Aerospace Research Institute should simulate enthalpy condition at a flight condition. SETF is a blow-down type, high-enthalpy wind tunnel. To attain a flight condition, a highly stagnated air comes into the test cell through a supersonic nozzle. Also, an air ejector of the SETF is used for simulating altitude conditions of the engine, and facility starting. SETF has a free-jet type test cell and this free-jet type test cell can simulate a boundary layer effect between an airplane and engine using facility nozzle, but it is too difficult to predict the nature of the facility. Therefore it is required to understand the starting characteristics of the facility by experiments. In this paper, the starting characteristics of the SETF and modifications of the ejector are described.
Study on the effect of Jet Fuel alteration on Turbine Engine Performances through Turbine Engine Test
Kim, You-Il ; Min, Seong-Ki ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 2, 2011, Pages 23~28
The engine ground and altitude tests were carried out to investigate the effect of jet fuel alteration on the performance of a small turbojet engine. JP-S was supplied 8% higher than JP-8 by fuel metering system at the same command. The employment of JP-S showed the similar starting characteristic to that of JP-8, however, difference in the ignition time and acceleration rate of engine speed due to the difference of fuel flow rate by fuel metering system was observed. In spite of jet fuel alteration, the test results yield the similar steady-state engine performance in net thrust, air flow, exhaust gas temperature, etc. On the other hand, the fuel consumption of JP-S increased by 5 % compared with that of JP-8. In point of specific fuel consumption (SFC), SFC of JP-S was approximately 1.1~2.6 %, 5 % higher than that of JP-8 in ground and altitude tests respectively at the same thrust.
Visualization of Roll Torque Generating Flows in a SRM Submerged-Nozzle by Cold Air-flow Test
Kim, Do-Hun ; Lee, In-Chul ; Lee, Yeol ; Koo, Ja-Ye ; Kang, Moon-Jung ; Kim, Yoon-Gon ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 2, 2011, Pages 29~35
The behaviors of combustion-induced internal flows of SRM equipped with fin-slot grain and submerged nozzle are very complex and diverse. Cold air-flow tests for 2D and 3D scale models of SRM have been done in order to specify the visualization method to analyze particular internal flow patterns such as roll-torque inducing flow. Swirl flow induced by asymmetric vortical tubes also has been visualized through employing various light source and recording directions.
Numerical Analysis on the Effect of Blade Sweep and Lean on the Performance of a Partial Admission Supersonic Turbine
Kwon, Tae-Un ; Jeong, Soo-In ; Cho, Jong-Jae ; Kim, Kui-Soon ; Jeong, Eun-Hwan ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 2, 2011, Pages 36~43
The present study deals with numerical flow analysis to investigate the effect of sweep and lean on the performance characteristics of a partial admission supersonic turbine. The flow analysis was performed for three different angles. The angles of sweep and lean are
. The results of the flow analysis showed that the efficiency is improved as the sweep angle is increased. However, a sweep angle of
was less effective in comparison with the baseline model. The total pressure loss was reduced as the lean angle is increased, but the total to static efficiency was decreased.
Life Prediction of Copper Alloy of Combustion Chamber
Lee, Keum-Oh ; Ryu, Chul-Sung ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 2, 2011, Pages 44~49
A study of the fatigue life of copper alloy which was used in inner jacket of regenerative cooling chamber of liquid rocket engine has been performed. Generally used life prediction methods -original universal slopes method, modified universal slopes method, Mitchell's method, B
umel and Seeger's method, and Ong's method- have been used for predicting the fatigue data. It was found that the novel life prediction method which was modified from Ong's method was suggested since almost all data have not been predicted well with the widely used methods. The suggested modified Ong's method predicted well within 3X scatterbands.
Strength Experimets on Head and Cooling Channel Specimens of a Preburner
Yoo, Jae-Han ; Moon, In-Sang ; Lee, Soo-Yong ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 2, 2011, Pages 50~55
A preburner for the high performance, staged combustion cycle liquid rocket engine is being developed. For the structural design processes, strength experiments and finite element analyses on specimens simulating the brazing joints of the preburner, were performed and compared. Total two kinds of the specimen were manufactured for the tests. One simulated the joints between the oxygen injectors and the head junctioned by the conventional vacuum brazing. The another was made to test the brazing surfaces by vacuum compression between the combustion chamber cooling channel and the outer wall. During the burst experiments, it was observed that the fractures were occurred not at the brazed joining but in the middle of the face plate and the cooling wall. In addition, the analysis showed that the predicted fracture locations and the strains were well matched with the experiment results.
Performance Test of Turbopump Assembly for 75 Ton Liquid Rocket Engine Using Model Fluid
Hong, Soon-Sam ; Kim, Jin-Sun ; Kim, Dae-Jin ; Kim, Jin-Han ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 2, 2011, Pages 56~61
Performance test of a full-scale turbopump assembly for a 75 ton class liquid rocket engine was carried out at full speed. Model fluid was used as a working medium: liquid nitrogen for the oxidizer pump, water for the fuel pump, and hot air for the turbine. The turbopump was operated stably, satisfying the performance requirements. Head coefficient and flow coefficient of the pumps remained constant at the speed-increasing period. In terms of performance characteristics of pumps and turbine, the results from the turbopump assembly test showed a good agreement with those from the turbopump component tests.
A Study of Separation Mechanism in Ball Type Separated Bolt
Lee, Yeung-Jo ; Koo, Song-Hoe ; Jang, Hong-Bin ; Lee, Bang-Eop ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 2, 2011, Pages 62~67
Launching tube is a kind of case to protect the guided weapons from external environments and conducted as a guide when they are fired. The guided weapons have been firmly kept at the launching tube and transferred, and would be separated at the required time when they are fired To meet the aim, it has been used explosive bolts which are reliable and efficient mechanical fastening devices having the special feature of a built-in release. The disadvantage of explosive bolt lies in that it is based on the high explosive effect of a pyrotechnic charge. When the explosive bolt is ignited, there are some bad effects; a flame, fragments and pyro-shock. Because of these bad effects there are many restriction to use bolt as joining devices to precision guided weapons. To solve these problems, the aim of the present work is to invent the ball-type separation bolt which is a pyrotechnically releasable mechanical linking device for two mechanical elements that does not suffer from such drawbacks. A standard pressure cartridge can moreover be easily integrated inside the device according to the present work and this with no modification to its structure. The present work was represented quantitatively the margin of separation safety and analysed separation mechanism in ball type separating bolt to perform the dynamic separation test.
Development of Nitrogen Supply System for Launch Complex of KSLV-I
Cho, Kie-Joo ; Ahn, Kyu-Bok ; Kim, Mun-Ki ; Kang, Sun-Il ; Ra, Seung-Ho ; Oh, Seung-Hyub ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 2, 2011, Pages 68~73
For the launch preparation of KSLV-I, gaseous nitrogen with various level of pressure and cryogenic liquid nitrogen are required. Nitrogen Supply System on launch complex has been developed to perform the production of high pressure gaseous nitrogen, the production of gaseous nitrogen with temperature of 273
2K for protection purge of launch vehicle after loading of propellant and the supply of cryogenic liquid nitrogen for cooling of fuel (kerosene) and oxidizer (liquid oxygen). The operational instability of vaporizer mainly caused by its heat transfer characteristics which sensitively depends on the atmospheric conditions was removed by introducing parallel installation of two vaporizer and their switching operation. The developed Nitrogen Supply System carried out its function successfully in preparation of KSLV-I flight tests.
Investigation of Control Theory on Pressure Drop Characteristics of Pneumatic Regulator for Gas Supply
Cho, Nam-Kyung ; Chung, Yong-Gahp ; Cho, In-Hyun ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 2, 2011, Pages 74~83
For launcher applications, different from other applications, very high flow rate is required which can lead to supply pressure drop against required setting pressure. The supply pressure decrease is closely related to regulator characteristics. In this paper, supply pressure offset is investigated considering regulators as kinds of control systems. Pressure offset of self-operated regulator is analyzed with sensitive parameter defined as the ratio of valve travel to pressure offset. It is shown that pressure offset of self-operating regulator can be improved by incorporating proportional and integral controls and they can be materialized with pilot regulator systems.