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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 17, Issue 6 - Dec 2013
Volume 17, Issue 5 - Oct 2013
Volume 17, Issue 4 - Aug 2013
Volume 17, Issue 3 - Jun 2013
Volume 17, Issue 2 - Apr 2013
Volume 17, Issue 1 - Feb 2013
Selecting the target year
A Numerical Study on Combustion-Response Parameters of Impinging-Jet Injectors for Stability Rating
Son, Jin Woo ; Kim, Chul Jin ; Sohn, Chae Hoon ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 2, 2013, Pages 1~8
DOI : 10.6108/KSPE.2013.17.2.001
This study presents relations between the time lag and interaction index of the impinging-jet injectors using the time lag model in a model chamber. The response of the flame is analyzed to artificial perturbation with 5% amplitude of oxidizer speed at a resonance frequency. At the mixing point of fuel and oxidizer, which determines the characteristic length, the relationship between velocity perturbation and heat release rate is quantified by combustion parameters of interaction index and time lag. In this method, time lag or delay is calculated by the characteristic length and the average velocity obtained from numerical results. The tendency that the time delay decreases with axial jet velocity has been observed.
Effect of Spiral Turbulent Ring on Detonation Performances of Acetylene-Oxygen Mixture
Son, Min ; Seo, Chanwoo ; Lee, Keon Woong ; Koo, Jaye ; Smirnov, N.N. ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 2, 2013, Pages 9~15
DOI : 10.6108/KSPE.2013.17.2.009
An effect of a spiral turbulent ring, so-called Shchelkin spiral, on a detonation performance was studied experimentally for acetylene and oxygen mixture. A couple of dynamic pressure transducers were used to calculate a detonation wave velocity by a time difference between two pressure peaks. In addition, impulse was measured by a load cell and the impulse was used to analyze the spiral effect on the detonation performance. A CFD analysis was adopted to calculate mass flow rates of the propellants and the minimum filling time. The maximum velocity and pressure were measured at the equivalence ratio of 2.4, and the measured values showed similar trend to C-J conditions calculated from CEA. For the shorter chamber with the short spiral, the maximum detonation velocity was appeared. In contrast, the longer chamber without the spiral showed the maximum thrust performance.
Effects of the Equivalence Ratio on Propagation Characteristics of CH
-Air Premixed Flame Intervened by an Ultrasonic Standing Wave
Seo, Hang Seok ; Lee, Sang Shin ; Kim, Jeong Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 2, 2013, Pages 16~23
DOI : 10.6108/KSPE.2013.17.2.016
An experimental study has been conducted to investigate the effects of equivalence ratio on the propagation characteristics of
-air premixed flame intervened by an ultrasonic standing wave. A Schlieren photography was used for the flame structure visualization, and the flame propagation behavior was investigated in detail throughout the post-processing analysis. It is found that the structural variation of methane/air premixed flame caused by the intervention of ultrasonic standing wave give rise to the enhancement of combustion reaction and flame propagation velocity. Effectiveness of the standing wave on the flame velocity decreases as the equivalence ratio increases. Larger flame velocity with the standing wave becomes undistinguishable in a specific range of equivalence ratios.
A Study of the Effect of Operating Time of a Rocket Motor on the Convective Heat Transfer Coefficient of Nozzle
Kim, Jinsoo ; Kim, Kyungsik ; Cho, Seunghwan ; Kwon, Youngdoo ; Kwon, Soonbum ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 2, 2013, Pages 24~30
DOI : 10.6108/KSPE.2013.17.2.024
To guarantee the exact control of missile warhead, it is inevitable to ensure the stabilities in the view points of structural and fluid/thermo dynamics of the rocket motor. Specially, despite of shortness in operating time of the rocket motor which is initial turning type of missile, it occurs frequently some problems of ablation at the neighborhood of the nozzle throat, with the result that the system itself gets to failure. In these connections, in the present study, the effect of the operating time of a rocket motor on the coefficient of convective heat transfer at the nozzle wall is investigated by numerical analysis. As a result, it is turned out that the heat transfer coefficient is largest at the just ahead of nozzle throat and decreases with the increase of operating time of the rocket motor. Furthermore, we found that the radius of curvature of throat becomes smaller, the maximum coefficient of convective heat transfer becomes larger.
Failure Behavior of Pin-jointed Composites under Hygrothermal Environments
Kim, Changyu ; Hwang, Youngeun ; Yoon, Sungho ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 2, 2013, Pages 31~38
DOI : 10.6108/KSPE.2013.17.2.031
This research analyzed the acoustic emission signals collected from the pin loading tests and investigated the effect of hygrothermal exposure on the fracture behavior of the pin-jointed carbon fiber/epoxy composites. The composite specimens include: the Base specimen that has not been exposed to any environments, the RT specimen that has been immersed in room temperature water, and the HT specimen that has been immersed in high temperature water. According to the pin loading test, the RT and the HT specimens showed 2.2% and 13% decreases in the bearing strength compared to the Base specimen, respectively. The analysis of the acoustic emission signals showed different fracture acceleration points for three types of the specimens. Furthermore, for the RT and the HT specimens, the event from the matrix crack signals in the composites decreased. This shows the effect of the hygrothermal conditions on the acoustic emission signals. Additionally, upon investigating the fracture behaviors of the pin-jointed composites, the exposing specimens to hygrothermal environments decreases the interfacial characteristics of the composites.
An Experimental Study of Laser-induced Ignition of Solid Propellant with Strand Burner
Lee, Sanghyup ; Ko, Taeho ; Yang, Heesung ; Yoon, Woongsup ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 2, 2013, Pages 39~45
DOI : 10.6108/KSPE.2013.17.2.039
Basically, in order to apply solid propellant as ignition source to high energy metal particle combustion system, we analyzed combustion characteristics of the HTPB/AP/Al, HTPE/AP/Al propellants by using a strand burner. The propellants were tested in a high-pressure windowed strand burner, which was pressurized up to 300 psia with pure argon gas. Strand burner was visualized with two quartz windows and ignition was accomplished by a 10 W
laser. The burning rate of propellant was measured with high-speed camera method for frame analysis and photodiode method for combustion time analysis. Emission spectrum was measured with spectrometer at 300 nm ~ 800 nm and 1500 nm ~ 5000 nm and then we analyzed species during propellant combustion.
Design and Analysis of Test Facility for the Experiment of Transpiration Cooling in Hot-flow Condition
Lee, Jungmin ; Na, Jaejeong ; Kang, Kyoungtaik ; Kwon, Minchan ; Hwang, Kiyoung ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 2, 2013, Pages 46~56
DOI : 10.6108/KSPE.2013.17.2.046
The test facility with hot-air supply system is required to develop transpiration cooling materials and experimentally evaluate its performance. In the study, the facility consists of an arc-plasma generator, plenum chamber suppling cold air, and test section was designed and an internal flow analysis was executed. From CFD results, it was confirmed that the designed plenum chamber thermally safeties and ideally mixes with plasma gas and cold air in the chamber. In addition, validity of design for supplying homogeneous flow to the test section was confirmed by this analysis.
Fracture Toughness Evaluation of a Solid Propellant Considering Viscoelasticity
Ha, Jaeseok ; Kim, Jaehoon ; Jung, Gyoodong ; Park, Jaebeom ; Yang, Hoyoung ; Seo, Bohwi ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 2, 2013, Pages 57~62
DOI : 10.6108/KSPE.2013.17.2.057
A crack in a solid propellant increases the area of burning surface, which leads to excessive burning that causes motor failure. Therefore, it is necessary to evaluate fracture toughness of solid propellants. However, it is very difficult to measure fracture toughness of solid propellants because of the nonlinear mechanical behavior. In this study, evaluation of fracture toughness on a solid propellant was carried out under the assumption that the solid propellant is a linear viscoelastic material. Actual displacements from fracture toughness tests using CCT specimens were converted into pseudo-elastic displacements by using stress relaxation characteristics and fracture toughness was evaluated using ASTM E399 standard. Also, effects of test temperature and speed on the fracture toughness were considered.
Numerical Study on the Flow Characteristics of a Side Jet Thruster Having Variable Thrust with a Rectangular Nozzle
Kim, Lina ; Sung, Hong-Gye ; Jeon, Young-Jin ; Cho, Seunghwan ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 2, 2013, Pages 63~70
DOI : 10.6108/KSPE.2013.17.2.063
To analyze flow characteristics of the side jet thruster with 4 shutters and rectangular nozzles, a 3-D simulation has been implemented. Numerical calculations for two rotation angles of the shutter, have been conducted. Internal recirculation in a chamber and asymmetric flow structure in a nozzle were observed. In addition, the more shutter rotated, the more asymmetries of flow increased, and this phenomena resulted in thrust bias. The degrees of thrust bias and thrust performance with the rotation angles of the shutter were predicted and compared with theoretical thrust.
Study on Condition Monitoring of 2-Spool Turbofan Engine Using Non-Linear GPA(Gas Path Analysis) Method and Genetic Algorithms
Kong, Changduk ; Kang, MyoungCheol ; Park, Gwanglim ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 2, 2013, Pages 71~83
DOI : 10.6108/KSPE.2013.17.2.071
Recently, the advanced condition monitoring methods such as the model-based method and the artificial intelligent method have been applied to maximize the availability as well as to minimize the maintenance cost of the aircraft gas turbines. Among them the non-linear GPA(Gas Path Analysis) method and the GA(Genetic Algorithms) have lots of advantages to diagnose the engines compared to other advanced condition monitoring methods such as the linear GPA, fuzzy logic and neural networks. Therefore this work applies both the non-linear GPA and the GA to diagnose AE3007 turbofan engine for an aircraft, and in case of having sensor noise and bias it is confirmed that the GA is better than the GPA through the comparison of two methods.
Experimental Study of the Thrust Vectoring Characteristics in a Two-Dimensional Convergent-Divergent Nozzle
Yu, Du Whan ; Choi, Seong Man ; Oh, Seong Hwan ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 2, 2013, Pages 84~93
DOI : 10.6108/KSPE.2013.17.2.084
Stealthy, high maneuverability and super cruise abilities are required for the next generation fighter and unmanned aircraft. Thrust vector control technique currently come into use to meet these requirements. In this experimental study, axial and pitch thrust were measured and Schlieren visualization were carried out using the scaled two dimensional thrust vector nozzles under various pitch deflection angle, pitch flap length and height. From the study, we could get the supersonic flow characteristics and draw an optimum geometric configuration of the two dimensional thrust vector nozzle.
Numerical Study of the Thrust Vectoring Characteristics in a Two-Dimensional Convergent Divergent Nozzle
Kang, Hyung Seok ; Choi, Seong Man ; Oh, Seong Hwan ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 2, 2013, Pages 94~104
DOI : 10.6108/KSPE.2013.17.2.094
A numerical analysis has been conducted to determine the pitch thrust vectoring characteristics of a two-dimensional convergent divergent exhaust nozzle for supersonic aircraft application. The numerical analysis was done by using Fluent and verified by the experimental test results. Analysis was performed with pitch angle of
each at the ambient temperature condition. To see the effect of a ratio of pitch flap length and pitch flap height, the ratio was varied from 0.5 to 2.5. The numerical analysis shows that pitch thrust is changed greatly with pitch flap length. The big difference of the pitch thrust with pitch flap length is due to the shock interactions in the nozzle.
Development of Numerical Model for Igniter and Study on Initial Ignition of Interior Ballistics
Sung, Hyung-Gun ; Jang, Jin-Sung ; Lee, Sang-Bok ; Choi, Dong-Whan ; Roh, Tae-Seong ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 2, 2013, Pages 105~113
DOI : 10.6108/KSPE.2013.17.2.105
A numerical model of the igniter for the interior ballistics has been developed by combining lumped parameter model with the theoretical equation of orifice. With the developed model of the igniter, the numerical study on characteristics of the interior ballistics has been conducted according to the igniter configuration in terms of igniter length, side hole diameter, and distribution of side holes. As results of the calculation of the pressure difference between the breech and shot base, the low-cycle oscillations have been influenced by the igniter length, while the high-cycle oscillations have been affected by the side hole diameter and the distribution of side holes.
An Analytical Study on a Heat Transfer Mechanism with Boiling Effect between Two Fluids in a Mini-channel
Yoo, YoungJoon ; Choi, Sangmin ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 2, 2013, Pages 114~121
DOI : 10.6108/KSPE.2013.17.2.114
In order to estimate the efficiency of an evaporative heat exchanger having mini channel, the equations to calculate heat exchanger properties, those are air temperatures and water temperatures etc, are derived from the governing equations based on the Navier-Stokes equation, even though there are several assumptions to make problem simplify. There are three heat transfer zones at the mini channel heat exchanger depending on the water condition. So, there are three governing equations and solutions to calculate the properties. As the results of this study, the equations to calculate a saturation point and a dry point are derived to evaluate an evaporative heat exchanger having micro channel. It is supposed to predict and evaluate the performance of a mini channel heat exchanger with evaporation of liquid.
Study on Pressure Fluctuations Observed in Combustion of Oxygen-Rich Preburners
Seo, Seonghyeon ; Kang, Sang Hun ; Lee, Soo-Yong ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 2, 2013, Pages 122~127
DOI : 10.6108/KSPE.2013.17.2.122
The paper includes the analytic results of pressure fluctuation data from the combustion of an oxidizer-rich preburner applicable to high-performance, closed-cycle liquid rocket engine systems. The combustion experiments went through two different steps of a chamber pressure during single run. Self-excited pressure fluctuations with a frequency of 78 Hz were observed only at the relatively low chamber pressure condition. These pressure fluctuations are regarded as a bulk mode. The intensity of pressure fluctuations by a root-mean-square value is 13.3% normalized by the chamber static pressure and no pressure excitation was observed at the design pressure condition. The bulk mode has an identical phase across the inside of the chamber and reveals the similar characteristics to the Helmholtz resonator.
Analysis of Dynamic Characteristics and Performance of Solenoid Valve for Pressurization Propellant Tank
Jang, Jesun ; Kim, Byunghun ; Han, Sangyeop ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 2, 2013, Pages 128~134
DOI : 10.6108/KSPE.2013.17.2.128
A 2-way solenoid valve regulates to maintain the pressure of ullage volume of propellant tanks when the command is given by control system for the liquid-propellant feeding system of space launch vehicle. The simulation model of solenoid valve for pressurization is designed with AMESim to verify the designs and evaluate the dynamic characteristics and pneumatic behaviors of valve. To improve the accuracy of the model, numerical flow analysis by using FLUNET code. The simulation results of their operating durations of valve by AMESim analysis are matched up with the results of experiments and validate valve model. Using the model, we analyze performance of valve; opening/closing pressure, operating time on various design factors of basic valve and control valve; geometrical size of valve seat, ratio of basic valve and sealing area.