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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
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Volume & Issues
Volume 11, Issue 6 - Dec 2007
Volume 11, Issue 5 - Oct 2007
Volume 11, Issue 4 - Aug 2007
Volume 11, Issue 3 - Jun 2007
Volume 11, Issue 2 - Apr 2007
Volume 11, Issue 1 - Feb 2007
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Numerical Study of Nonlinear Acoustic Damping Induced by Acoustic Resonators in a Rocket Combustor
Sohn, Chae-Hoon ; Park, I-Sun ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 2, 2007, Pages 1~8
Nonlinear acoustic damping of a half-wave acoustic resonator in a rocket combustor is investigated numerically adopting a nonlinear acoustic analysis. First, in a baseline chamber without any resonators, acoustic behavior is investigated over the wide range of acoustic amplitude from 80 dB to 150 dB. Damping factor increases nonlinearly with acoustic amplitude and nonlinearity becomes appreciable at acoustic amplitude above 125 dB. Next, damping effect of a half-wave resonator is investigated. It is found that nonlinear acoustic excitation does not affect optimum tuning condition of the resonator, which is derived from linear acoustics. A half-wave resonator is effective even for acoustic damping of high-amplitude pressure oscillation, but its function of acoustic damper is relatively weakened compared with the case of linear acoustic excitation.
Performance Test and Calculation of Recirculation Line in Propellant Feeding System
Kwon, Oh-Sung ; Cho, Nam-Kyung ; Chung, Yong-Gahp ; Han, Sang-Yeop ; Kim, Young-Mog ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 2, 2007, Pages 9~17
The performance test of recirculation line in propellant feeding system was carried out. Liquid oxygen was used as cryogenic propellant and helium was used as recirculation promotion gas. Tests were done in cases at atmospheric pressure and at pressure of 4 barg in the ullage space of propellant tank. Liquid oxygen recirculation flowrate with helium injection flowrate and temperature distribution along the line were measured. There was appropriate helium injection flowrate for gas-lift recirculation system. Test data were used to make calculation program by test data correlation method. In this paper the procedure of calculation was presented and the results were compared to test data.
Computational Study of the Passive Control of the Oblique-Shock-Interaction Flows
Chang, Sung-Ha ; Lee, Yeol ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 2, 2007, Pages 18~25
Computational study on the passive control of the oblique shock-wave/turbulent boundary-layer interaction utilizing slotted plates over a cavity has been carried out. The numerical boundary layer profile upstream of the interaction follows the compressible turbulent boundary-layer theory reasonably well, and the other results also show good agreements with the experimental observations, such as the wall surface pressures and Schlieren flow visualizations. Further, the effects of various slot configuration including number, location and angle of the slots on the characteristics of the interactions, such as the variation of the total pressures, the boundary-layer characteristics downstream of the interaction and the recirculating mass flux through the slots, are also tested and compared.
Effects of Solid Propellant Cases on the Thermal Response of Nozzle Liner
Hwang, Ki-Young ; Yim, Yoo-Jin ; Ham, Hee-Cheol ; Kang, Yoon-Goo ; Bae, Joo-Chan ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 2, 2007, Pages 26~36
The thermal response characteristics of nozzle liner for a solid rocket motor applying highly aluminized PCP or HTPB propellant with slotted tube grain have been investigated. The SEM photographs of aluminum oxide particles taken from nozzle liner show that the PCP propellant with the finer and less contents of oxidizer can offer greater possibility for increasing aluminum agglomeration than the HTPB propellant. The PCP propellant shows locally greater mechanical erosion at 4 circumferential areas of the nozzle entrance in line with grain slot due to the impingement of large particles, but the HTPB propellant shows greater thermochemical ablation at the nozzle blast tube, the throat insert and the exit cone because of relatively much more mole fraction of
in combustion gases.
Reactive Fields Analysis of End-Burning Hybrid Combustor Using Tangential Oxidizer Injectors with Various Momentum Ratio
Min, Moon-Ki ; Kim, Soo-Jong ; Kim, Jin-Kon ; Moon, Hee-Jang ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 2, 2007, Pages 37~46
In this study, combustion fields of the end-burning hybrid combustor with tangential oxidizer injectors are examined. Momentum ratio of oxidizer is used as a main parameter to analyse the combustion efficiency with temperature, pressure, swirl velocity and mixture fraction field. It was found that as momentum ratio decreases the overall combustion efficiency is enhanced with the pressure field being insensitive to momentum ratio keeping quasi-uniform distribution. Irrespective to the momentum ratio, annular hot region commonly occurred in the upper combustion chamber where this phenomenon was left for a future improvement to be followed.
Study on the Surface Heat Transfer Around a Circular Secondary Jet in the Supersonic Flow
Yi, Jong-Ju ; Yu, Man-Sun ; Cho, Hyung-Hee ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 2, 2007, Pages 47~53
Convective heat transfer coefficient was measured around a circular secondary jet ejected into the supersonic flow field. The wall temperature measurement around a injection nozzle was conducted using infra-red camera. The constant heat flux is applied to the wall around a secondary nozzle. According to jet to freestream momentum ratio, the injection flow penetrates into the supersonic flow field. The measured temperature is used to calculate the convective heat transfer coefficient.
Investigation on Temperature Drop during Pressurant Discharging from Pressurant Tank of Liquid Rocket Propulsion System (I)
Chung, Yong-Gahp ; Kwon, Oh-Sung ; Cho, Nam-Kyung ; Han, Sang-Yeop ; Cho, In-Hyun ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 2, 2007, Pages 54~61
Propellant pressurization system in liquid rocket propulsion system plays a role supplying pressurant gas at a controlled pressure into the ullage space of propellant tanks. The most important design parameter for such propellant pressurization system is the temperature of pressurant gas fed from pressurant tank. Such pressurant is gaseous state, of which density is very sensitive to the temperature of pressurant. Generally for the propulsion system, which requires high thrust and is consisted of cryogenic propellant the pressurant is stored at high density and high pressure to reduce the weight of pressurant tanks, which are placed inside of cryogenic propellant tank. That is called cryogenic storage pressurization system. This study investigates the temperature variation of pressurant at the time when the pressurant is coming out of pressurant tank experimentally as well as numerically. Fluids used in this study are air and liquid oxygen as outer fluid and gaseous nitrogen and gaseous helium as pressurant respectively.
A Study on Improvement of Aiming ability using Disturbance Measurement in the Firing Vehicle
Yoo, Jin-Ho ; Lee, Dong-Ju ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 2, 2007, Pages 62~70
The aiming ability is a to improve accuracy performance of the firing vehicle. This paper describes the detection method of chatter vibration using disturbance acceleration in the pointing structure. In order to analysis vibration trends of the pointing system occurred during vehicle drive, acceleration data was processed by using data processing algorithm with moving average and Hilbert transform. Specific mode constants of acceleration were obtained under various disturbances. Vehicle velocity, road condition, property of pointing structure were considered as factors which make change of vibration trend in vehicle dynamics. Finally, back propagation neural networks have been applied to the pattern recognition for the classification of vibration signal in various driving conditions. Results of signal processing were compared and analysed.
Performance Analysis of PE-GOX Hybrid Rocket Motor Part I : Regression Rate Characteristics
Youn, Chang-Jin ; Song, Na-Young ; Yoo, Woo-Jun ; Jeon, Chang-Soo ; Kim, Jin-Kon ; Sung, Hong-Gae ; Moon, Hee-Jang ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 2, 2007, Pages 71~78
An experimental investigation was conducted to clarify the combustion characteristics of Polyethylene-GOX(PE-GOX) hybrid motor using a single-port fuel grain configuration. Data from the experiments were analyzed to evaluate the length-averaged regression rate of PE-GOX propellants. Based on the existing theories, the empirical regression rate formulas provided from Marxman[3,4] and Altman showed good concordance with the PE-GOX experiments. The accuracy of the regression rate was then evaluated and compared with the measured one. As a result, Marxman's model was somewhat more precise than Altman's model in these experiments. Moreover, the consideration of the empirical regression rate showed that O/F ratio has minor variation due to the quasi constant inflow of the fuel during motor firing.
Combustion Characteristics and Performance Prediction of PE-GOX Hybrid Rocket Motor Part II : Internal Ballistic Performance
Yoon, Chang-Jin ; Song, Na-Young ; Yoo, Woo-Jun ; Jeon, Chang-Soo ; Kim, Jin-Kon ; Moon, Hee-Jang ; Sung, Hong-Gye ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 2, 2007, Pages 79~85
An internal ballistic model to predict the performance of a Polyethylene-GOX (PE-GOX) hybrid motor was proposed and evaluated. A theoretical treatment of the model was followed by detail discussion of each of the factors affecting the overall performance. The present model consists of the governing equations by considering the unsteady burn-back rate of the fuel grain and on-off response characteristics of a oxygen-supply valve. The numerical results using the 4th order Runge-Kutta scheme with temporal physicochemical properties showed good agreements with test results and the global effects of the performance parameters, such as the burning area of the fuel grain, O/F ratio, and etc., on the performance of the motor were analyzed.