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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 16, Issue 6 - Dec 2012
Volume 16, Issue 5 - Oct 2012
Volume 16, Issue 4 - Aug 2012
Volume 16, Issue 3 - Jun 2012
Volume 16, Issue 2 - Apr 2012
Volume 16, Issue 1 - Feb 2012
Selecting the target year
Interacting Effects of an Ultrasonic Standing-wave on the Propagation Behavior and Structural Stabilization of Propane/Air Premixed Flame
Lee, Sang Shin ; Seo, Hang Seok ; Kim, Jeong Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 6, 2012, Pages 1~8
DOI : 10.6108/KSPE.2012.16.6.001
An experimental study has been conducted to scrutinize into the influence of ultrasonic standing wave on the propagating behavior and structural stabilization of propane/air premixed flame at various equivalence ratios in half-open rectangular duct. Evolutionary features of the flame fronts are caught by high-speed images, and the variation of flame structure and local flame velocities along the propagation are analyzed. It is revealed that the propagation velocity agitated by the ultrasonic standing wave is greater than that without the agitation: the velocity enhancement diminishes as the equivalence ratio approaches the stoichiometric. Influence of standing wave on the flame overwhelms that of the buoyancy which slants the flame front towards top of the duct, and thus the standing wave contributes to the structural stabilization of propane/air premixed flame.
Effect of Orifice Length on Particle Distribution in Particle-laden Jet
Yoon, Jungsoo ; Paik, Kyong-Yup ; Khil, Taeock ; Yoon, Youngbin ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 6, 2012, Pages 9~15
DOI : 10.6108/KSPE.2012.16.6.009
As a propellant of a high speed underwater vehicle, the hydro-reactive solid metal particles using seawater as a oxidizer maximizes its specific impulse when the solid metal particles and the seawater are uniformly mixed in the combustion chamber. The purpose of this study is to investigate the effects of injector geometry on the particle distribution of similarity point of view. For the purpose of this similarity of the mean velocity and particle number density along the radial direction was measured by Particle Image Velocimetry(PIV).
A Trade-off Analysis between Combustion and Cooling Performance of a Liquid Rocket Combustor with Fuel Film Cooling Scheme
Joh, Miok ; Kim, Seong-Ku ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 6, 2012, Pages 16~22
DOI : 10.6108/KSPE.2012.16.6.016
Performance of a liquid rocket thrust chamber with regenerative cooling scheme has been numerically analyzed using in-house CFD code which can predict combustion/cooling performance and provide nozzle design parameters. This paper investigates trade-offs between combustion and cooling performance with varying amount of fuel directly injected into the chamber wall to form cooling films and mixture ratios for the peripheral injectors. Further efforts to verify/improve the simulation methodology including comparison with the firing test results are planned to make it a reliable tool to optimize the film cooling and other major design parameters.
Rheological Characteristics of Kerosene Gel Fuel with SiO
Kim, Jaewoo ; Jun, Doosung ; Kang, Teagon ; Jang, Seok Pil ; Koo, Jaye ; Moon, Heejang ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 6, 2012, Pages 23~31
DOI : 10.6108/KSPE.2012.16.6.023
Present work deals three families of
gelling agents which have been used to produce gel fuel based on Kerosene. Jet A-1 is chosen as fuel where power-law rheological model is used to confirm whether or not the gelification is achieved depending on the %wt of gellant. It was confirmed that the produced jelly-like substance have shear-thinning effect, and that its apparent viscosity increases as
concentration increases. Compared to other gellants, gel with Aerosil(R) R972 fits most to the power-law model, while gels with Silica 230 and Silica 530 deviate from the power-law model. The rheological characteristics behaved differently depending on the mixing method(vortex mixing and manual mixing) when gellant concentration is increased.
Thermoacoustic Analysis Model for Combustion Instability Prediction - Part 1 : Linear Instability Analysis
Kim, Daesik ; Kim, Kyu Tae ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 6, 2012, Pages 32~40
DOI : 10.6108/KSPE.2012.16.6.032
For predicting eigenfrequency and initial growth rate of combustion instabilities in lean premixed gas turbine combustor, linear thermoacoustic analysis model was developed in the current paper. A model combustor was selected for the model validation, which has well-defined inlet and outlet conditions and a relatively simple geometry, compared to the combustor in the previous works. Analytical linear equations for thermoacoustic waves were derived for a given combustion system. It was found that the prediction results showed a good agreement with the measurements, even though there was underestimation for instability frequencies. This underestimation was more obvious for a longer flame (i.e. wider temperature distribution) than for a shorter flame.
Thermoacoustic Analysis Model for Combustion Instability Prediction - Part 2 : Nonlinear Instability Analysis
Kim, Daesik ; Kim, Kyu Tae ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 6, 2012, Pages 41~47
DOI : 10.6108/KSPE.2012.16.6.041
It is very important to predict the nonlinear behavior of combustion instability such as transition phenomena and limit cycle amplitude for fully understanding and controlling the instabilities. These nonlinear instability characteristics are highly dependent upon the flames` nonlinear dynamics in a gas turbine premixed combustor. In this study, nonlinear instability TA(Thermo-acoustic) models were introduced by applying the concept of flame describing function to the thermoacoustic analysis method. As a result of model development, for a given combustor length, the growth rate of instability was greatly affected by the change in amplitude, although the instability frequency was not. Further researches under various operating conditions and model validation on limit cycle amplitude are required.
Steady-state Thrust Characteristics of Hydrazine Thruster for Attitude Control of Space Launch Vehicles
Kim, Jong Hyun ; Jung, Hun ; Kim, Jeong Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 6, 2012, Pages 48~55
DOI : 10.6108/KSPE.2012.16.6.048
An ambient hot-firing test was carried out for the hydrazine thruster which may be employed in the space launch vehicles. The thruster is designed to produce 67 N (15
) of nominal steady-state thrust at an inlet pressure of 2.41 MPa (350 psia). A scrutiny into the performance characteristics of thruster is made in terms of thrust, propellant supply pressure, mass flow rate, chamber pressure, and temperature at the steady-state firing mode. As a result, it is ensured that the practical performance efficiencies are above 89.1% compared to its ideal requirements.
Fuel-Side Cold-Flow Test and Pressure Drop Analysis on Technology Demonstration Model of 75 ton-class Regeneratively-Cooled Combustion Chamber
Ahn, Kyubok ; Kim, Jong-Gyu ; Lim, Byoungjik ; Kim, Munki ; Kang, Donghyuk ; Kim, Seong-Ku ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 6, 2012, Pages 56~61
DOI : 10.6108/KSPE.2012.16.6.056
Fuel-side cold-flow tests were performed on the technology demonstration model of a 75 ton-class liquid rocket engine combustion chamber for the first stage of the Korea space launch vehicle II. Pressure drop in the cooling channels of the combustion chamber was measured by changing fuel mass flow rate through a pressure regulating system. Pressure drop in each segment of the chamber could be obtained and a lot of pressure drop was caused by high flow velocity in the nozzle throat segment. The accuracy of a hydraulic analysis method for calculating a pressure loss in cooling channels could be verified by applying it to the cold-flow test conditions.
Recent Progress in R&D and Prospect of Divert and Attitude Control System(DACS)
Kim, Seongsu ; Huh, Hwanil ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 6, 2012, Pages 62~72
DOI : 10.6108/KSPE.2012.16.6.062
Divert and attitude control system(DACS) plays an important role for orbit transfer and attitude control, and therefore becomes important subject for recent space vehicle and Precision Guided Missile(PGM) development. To develop DACS system, main research areas include shape combination of pintle and nozzle to maximize thrust change, and reduction of aerodynamic pintle load to minimizle pintle driving force, and development of multi-axis control algorithm. In this paper, introduction, classification, and overseas/domestic research and development program, and prospects of DACS are reviewed and summarized.
A Study on the Ignition Characteristics of Liquid Rocket Engine Thrust Chamber with Regenerative Cooling
Lee, Kwang-Jin ; Han, Yeoung-Min ; Kim, Jong-Gyu ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 6, 2012, Pages 73~78
DOI : 10.6108/KSPE.2012.16.6.073
The ignition characteristics of liquid rocket engine thrust chambers which have been developed by domestic technology were analyzed through hot-firing tests. Thrust chambers used in hot-firing tests have different characteristics in terms of the injector for ignition, film cooling method and the position of the oxidizer inlet. Also, these thrust chambers used their respective startup sequences. Analysis results showed that according to temperature profiles of the oxidizer manifold, low frequency fluctuation was appeared in ignition area. This low frequency fluctuation didn`t give rise to violent malfunction of the thrust chamber, but the continuous observation as a concern parameter in the side of interfaces with engine system and launch vehicle should be demanded.
A Study on Crack Propagation of Solid Propellant by Rapid Pressurization
Ha, Jaeseok ; Kim, Jaehoon ; Yang, Hoyoung ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 6, 2012, Pages 79~84
DOI : 10.6108/KSPE.2012.16.6.079
An experiment of rapid pressurization-induced crack propagation of solid propellant was conducted by using a windowed test chamber. A pre-cracked specimen of solid propellant is installed in the chamber, and highly compressed nitrogen gas in an accumulator pressurizes the chamber until the chamber pressure reaches set-up pressure to make the chamber depressurization. Pressure-time trace was obtained from the experimental result, and pressurization rate was defined from the trace. In this study, three pressurization rates (64.34, 73.86 and 85.44 MPa/s) are considered, and propagation lengths are measured. Also, a progression of the crack propagation recorded by a high-speed digital camera is presented.
Reaction of an Insensitive Munitions(IM) Igniter for Solid Propulsion System
Ryu, Byungtae ; Lee, Dohyung ; Ryoo, Baekneung ; Choi, Hongseok ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 6, 2012, Pages 85~91
DOI : 10.6108/KSPE.2012.16.6.085
This paper describes the results of study on reaction of insensitive igniter in which a pyrosensor is automatically sensing the rate of risk of fire or explosion of solid rocket motor exposed to an unexpected fire and makes the rocket motor burn itself safely. The Slow Cook Off(SCO) test following the regulation of MIL-STD-2105D was carried out with a rocket motor loaded with HTPB propellant, in which a thermal pyrosensor igniter was installed. The auto-ignition temperature measured was approximately
and it corresponded to Type V(Burning) reaction in SCO test, while the temperature by Kissinger equation was calculated to be
Modeling and Simulation of Combustion Chamber Test Facility Oxidizer Supply System
Chun, Yonggahp ; Cho, Namkyung ; Han, Yeoung-Min ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 6, 2012, Pages 92~97
DOI : 10.6108/KSPE.2012.16.6.092
The propulsion system of space launch vehicle generates thrust by supplying oxidizer and fuel to combustion chamber. KSLV-II 2nd stage engine, currently under development by KARI, is to use liquid oxygen as a oxidizer and JET-A1 as a fuel. The 2nd stage pump-fed engine is mainly composed of combustion chamber, turbo-pump and engine supply system. To develop liquid propulsion engine, the development of combustion chamber must be preceded. For performance validation of the combustion chamber, the designed and manufactured combustion chamber should be tested in combustion chamber test facility (CCTF). The detailed design for the planned CCTF in Naro Space Center was conducted. The oxidizer supply system modeling using AMESim was performed based on the results of the detailed design, and the oxidizer supply characteristics was analyzed in this paper.