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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 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
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A Numerical Analysis of Acoustic-Pressure Response of H
-Air Diffusion Flames with Application of Time-Lag Model
Sohn, Chae-Hoon ; Lim, Jun-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 1, 2012, Pages 1~8
DOI : 10.6108/KSPE.2012.16.1.001
Acoustic-pressure response of diluted hydrogen-air diffusion flames is investigated numerically by adopting a fully unsteady analysis of flame structures in low and high pressure regimes. As acoustic frequency increases, finite-rate chemistry is enhanced through a nonlinear accumulation of heat release rate for any pressure regime, leading to a high amplification index. Same numerical results are analyzed with application of a pressure-sensitive time lag model, and thereby, interaction index and time lag are calculated for each pressure regime. The interaction index has the largest value in each pressure regime at an acoustic frequency near 1000 Hz. In a high-pressure regime, flames are more unstable than in a low-pressure regime. The interaction index shows a good agreement with the amplification index.
Performance Prediction Method of Hybrid Rocket Motors with Local Variance of Combustion
Cho, Min-Gyung ; Heo, Jun-Young ; Park, Hyung-Ju ; Kim, Jin-Kon ; Moon, Hee-Jang ; Sung, Hong-Gye ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 1, 2012, Pages 9~15
DOI : 10.6108/KSPE.2012.16.1.009
An unsteady internal ballistic performance model was proposed to take account for the variance of local regression rate along the grain port of a hybrid rocket combustor. The characteristic parameters of hybrid rocket motor was investigated. The performance model of concern in the study was fairly comparable with the test result. The combustion coefficients and local burning characteristics of a hybrid rocket motor were evaluated. The local variation of the oxidizer mass flow rate results in the changes of local regression rate, pressure, temperature, and gas velocity to flow direction, which was analyzed quantitatively.
Conceptual Design Study of Two-Stage Hypersonic Scramjet Vehicle
Lee, Kyung-Jae ; Kang, Sang-Hun ; Yang, Soo-Seok ; Park, Chul ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 1, 2012, Pages 16~24
DOI : 10.6108/KSPE.2012.16.1.016
In this study, two-stage hypersonic scramjet vehicle was designed for the flight condition of Mach number 6. In order to launch at sea level, two stage concept was applied. The first stage of the vehicle is solid rocket-powered and is mounted under the second stage. The second stage is powered by scramjet propulsion system and gas wings. The suggested mission scenario is to deliver 0.2 ton payload to the range of 2,000 km. For the first step of conceptual design, trajectory of air vehicle was calculated by 3-DOF trajectory code. Based on the result of trajectory code, scramjet engine design and mass estimation were performed by non-equilibrium nozzle flow code and NASA's HASA model, respectively. In order to find best solution, all steps of designing process was iterated until they was reached.
Improvement of the Aerothermal Environment for a 90° Turning Duct by an Endwall Boundary Layer Fence
Cho, Jong-Jae ; Kim, Kui-Soon ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 1, 2012, Pages 25~35
DOI : 10.6108/KSPE.2012.16.1.025
An endwall boundary layer fence technique was adapted to improve the aerothermal environment of a gas turbine passage. The shape optimization of the fence was performed to maximize the improvement. The turbine passage was simulated by a
turning duct (ReD=360,000). The main purpose of the present investigation was to focus on finding a endwall boundary layer fence with minimum total pressure loss in the passage and heat transfer coefficient on the endwall of the duct. Anothor objective function was to minimize the area on the endwall of the duct. An approximate optimization method was used for the investigation to secure the computational efficiency. Results indicated that a significant improvement in aerodynamic environment can be achieved through the application of the fence. Improvement of the thermal environment was smaller than that of the aerodynamic enviroment.
Design and Cold Flow Test of a Multi-injector Engine using Hydrogen Peroxide/Kerosene
Lee, Yang-Suk ; Jeon, Jun-Su ; Ko, Young-Sung ; Kim, Yoo ; Kim, Sun-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 1, 2012, Pages 36~44
DOI : 10.6108/KSPE.2012.16.1.036
Multi-injector rocket engine using high-concentrated hydrogen peroxide and kerosene was designed and manufactured. Design requirements of a rocket engine were determined and main geometrical parameters of rocket engine were determined on the basis of fundament. Six coaxial swirl injectors were mounted on the multi-injector engine. Flow analysis in the hydrogen peroxide manifold was performed to minimize stagnation and recirculation zones. Finally, the optimized hydrogen peroxide manifold was manufactured and cold flow test was carried out to confirm mass flow rate per uni-element, spray pattern and atomization characteristics. The results of cold flow test showed that the mixing head design process was successful and enough to use as a essential database for the development of a full-scale engine.
Optimization of an Asymmetric Trapezoidal Fin Based on the Fixed Fin Base Height
Song, Nyeon-Joo ; Kang, Hyung-Suk ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 1, 2012, Pages 45~54
DOI : 10.6108/KSPE.2012.16.1.045
Optimization of the asymmetric trapezoidal fin with various upper lateral surface slope is made using a two-dimensional analytic method. For the fixed fin base height, the optimum heat loss, fin length and effectiveness are represented as inner fluid convection characteristic number, fin base thickness, fin base height, fin shape factor and ambient convection characteristic number. For this optimum procedure, the optimum heat loss is defined as 95% of the maximum heat loss from the fin. One of the results shows that optimum heat loss and effectiveness seems independent of the fin shape factor while optimum fin length decreases almost linearly as the fin shape factor increases.
RANS-LES Simulations of Scalar Mixing in Recessed Coaxial Injectors
Park, Tae-Seon ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 1, 2012, Pages 55~63
DOI : 10.6108/KSPE.2012.16.1.055
The turbulent flow characteristics in a coaxial injector were investigated by the nonlinear
model of Park et al. and large eddy simulation (LES). In order to analyze the geometric effects on the scalar mixing for nonreacting variable-density flows, several recessed lengths and momentum flux ratios are selected at a constant Reynolds number. The nonlinear
�� model proposed the meaningful characteristics for various momentum flux ratios and recess lengths. The LES results showed the changes of small-scale structures by the recess. When the inner jet was recessed, the development of turbulent kinetic energy became faster than that of non-recessed case. Also, the mixing characteristics were mainly influenced by the variation of shear rates, but the local mixing was changed by the adoption of recess.
A Design Study on a Phase Change Heat Exchanger of an Environmental Control System for a POD
Yoo, Yung-Jun ; Min, Seong-Ki ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 1, 2012, Pages 64~71
DOI : 10.6108/KSPE.2012.16.1.064
While a conventional ECS mainly consisted of an air cycle machine and heat exchangers, a new concept of a phase change heat exchanger was added to improve the transient performance of the ECS. As a result, an ECS modeling program including the phase change heat exchanger is newly developed to estimate its effect in various flight conditions such as take-off, maneuver, cruise, and landing. The simulation result regarding a virtual flight profile has confirmed the new ECS fulfilled the requirement by showing the temperature of the cooling air returned from the bay was always kept below
. Through this study, the new ECS concept with PCHE was verified successfully.
Study on the Propellant Position for the Decrease of the Differential Pressure in the Interior Ballistics of a Gun Propulsion System
Jang, Jin-Sung ; Sung, Hyung-Gun ; Roh, Tae-Seong ; Choi, Dong-Whan ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 1, 2012, Pages 72~78
DOI : 10.6108/KSPE.2012.16.1.072
The position effect of the solid propellant in the combustion chamber on the decrease of the differential pressure has been investigated using the IBcode. Generally the metallic cartridge or CCC (combustible cartridge case) are used to load the propellant of the gun propulsion system. The position of the cartridge(propellant) is, therefore, a major factor for the interior ballistics in case the combustion chamber is larger than the cartridge. In this study, three different positions in the empty space of the chamber have been considered. As results, the case of the propellant located in the region near the base and breech has shown that the negative differential pressure and the difference between the breech pressure and the base pressure are much higher than those of the case of the propellant located in the center of the chamber. The case of the propellant in the center of the chamber is, therefore, more profitable to improve the performance of the interior ballistics.
The Trend of New Technology in Metal Spinning
Lee, Tae-Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 1, 2012, Pages 79~85
DOI : 10.6108/KSPE.2012.16.1.079
This study investigates mainly on the technical development trend through the published papers, such as asymmetric metal spinning, metal spinning in heat treatment conditions and free mandrel spinning. Although the classical spinning, so called conventional, shear, tube spinning, uses the axisymmetric shaped mandrel(which is same inner shape of the final product), in new technologies the mandrel can be asymmetric one, spinning can be done without mandrel and also spinning is done with heat treatment together.