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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
Editor in Chief :
Volume & Issues
Volume 9, Issue 4 - Dec 2005
Volume 9, Issue 3 - Sep 2005
Volume 9, Issue 2 - Jun 2005
Volume 9, Issue 1 - Mar 2005
Selecting the target year
Development of Chemical Equilibrium CFD Code for Performance Prediction and Optimum Design of LRE Thrust Chamber
Kim Seong-Ku ; Moon Yoon Wan ; Park Tae-Seon ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 1, 2005, Pages 1~8
An axisymmetric compressible flow solver accounting for chemical equilibrium has been developed as an analysis tool exclusively suitable for performance prediction and optimum contour design of LRE thrust chamber. By virtue of several features focusing on user-friendliness and effectiveness including automatical grid generation and iterative calculations with changes in design parameters prescribed through only one keyword-type input file, a design engineer can evaluate very fast and easily the influences of various design inputs such as geometrical parameters and operating conditions on propulsive performance. Validations have been carried out for various aspects by detailed comparisons with the result of CEA code, experimental data of JPL nozzle, actual data for two historical engines, and ReTF data for KSR-III.
Heat Transfer on a Jet Vane Surface Installed in a Rocket Nozzle
Yu Man Sun ; Cho Hyung Hee ; Hwang Ki Young ; Bae Ju Chan ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 1, 2005, Pages 9~16
Jet vane is an useful component which is installed at the end of a nozzle for the purpose of the posture control and the secure controlling stability during the initial launching of a rocket. During several seconds from its initial launching moment, the JV driving part is heated due to the direct contact of the vane with the combusted gas and the vane is ablated mechanically or chemically. In this study, as the fundamental study for the thermal analysis of jet vane, the heat transfer into a jet vane which is located in the uniform supersonic flow field is calculated. For this, boundary layer integral method and finite difference method are used simultaneously. Based on the thermal boundary conditions derived from the analysis, the transient heat conduction in the vane is also calculated.
Investigation for Spray Characteristics of Dual Swirl Injector
Park Hee Ho ; Jeong Chung Yon ; Kim Yoo ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 1, 2005, Pages 17~26
Both numerical analysis and cold tests for the swirl coaxial type injector were performed to obtain the influence of spray angle, velocity ratio and liquid film thickness for pressure drop and recess. The basic experimental and numerical data obtained in this study can be applicable to the performance design of swirl coaxial type injector. Spray angle was not affected by the applied test pressure drop, but spray angle was affected by tangential velocity ratio and shape factors. Feasibility of numerical analysis for the liquid film thickness and spray angle was confirmed, and the change of liquid film thickness by tangential velocity ratio affected more seriously than pressure drop, and liquid film thickness was decreased with increasing tangential velocity ratio.
A Study of Interpretation of Separation Behavior in Gas Expansion Separation(GES) Bolt
Lee Young Jo ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 1, 2005, Pages 27~34
The present work has been developed the study of interpretation of separation behavior in gas expansion separation(GES) bolt which has the separation characteristics without fragmentation and minimum pyre-shock during the operation of the explosive bolt. In order to obtain the performance of minimum pyre-shock, the present work used non-compressive material instead of separation explosives. The use of the interpretation processor could be extensively helped to design the shape and the amount of explosives in the explosive bolt having complex geometry, and to analyse the separation behavior during the operation. It is also proved that the GES bolt is the most suitable the separation system necessary to minimum pyre-shock and non fragmentation compare with others.
Numerical Analysis of Rocket Exhaust Plume with Equilibrium Chemistry and Thermal Radiation
Shin Jae-Ryul ; Choi Jeong-Yeol ; Choi Hwan-Seck ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 1, 2005, Pages 35~45
Numerical study is carried out to investigate the effects of chemistry and thermal radiation on the rocket plume flow field at various altitudes. Navier-Stokes equations for compressible flows were solved by a fully-implicit TVD code based on the finite volume method. An infinitely fast chemistry module for hydrocarbon mixture with detailed thermo-chemical properties and a thermal radiation module for optically thick media were incorporated with the fluid dynamics code. The plume flow fields of a kerosene-fueled rocket flying at Mach number zero at sea-level, 1.16 at altitude of 5.06 km and 2.90 at 17.34 km were numerically analyzed. Results showed the plume structures at different altitude conditions with the effects of chemistry and radiation. It is understood that the excess temperature by the chemical reactions in the exhaust gas may not be ignored in the view point of propulsion performance and thermal protection of the rocket base, especially at higher altitude conditions.
Propeller Design of Unmanned Target Drone for the Performance Improvement
Lee Sangmyeong ; Sung Hyunggun ; Roh Taeseong ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 1, 2005, Pages 46~52
A propeller as a propulsion system has been redesigned to improve performance of a target drone. The vortex theory has been applied for the propeller design method. Design variables have been the chord length along the direction of blade radius, the change of blade radius, and the geometric angle of the blade. The existing propeller has been redesigned and modified considering engine RPM change to get the improved thrust at both low and high speeds.
Design and Evaluation of Vaned Pipe Bends of Liquid Propellant for Satellite Launch Vehicles
Lee Hee Joon ; Han Sang Yeop ; Ha Sung Up ; Kim Young Mog ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 1, 2005, Pages 53~60
The use of pipe-bends brings about non-uniform flows at the exit of them due to the velocity difference between inner and outer flows inside the bend. These phenomena may cause turbopump of satellite launch vehicle to run off-design and reduce its efficiency, and also introduce unstable influx of propellants to engine manifold after passing through a turbopump. In order to improve the uniformity of flow at the bend exit, certain turning vanes are set up in the bend pipe normally. Correspondingly the design is an
bend pipes that incorporate with the maximum three turning vanes. All designs were analyzed with numerical analysis by solving the Navier-Stokes equations in three dimensions in case of each respective fuel and oxidizer. Evaluations of the vaned pipe bends designs were accomplished by the velocity magnitude distributions and the predicted pressure drops. We could find that the more vaned bend pipe and larger angle pipe under consideration effectively, the more uniform velocity magnitude of the bend and pressure losses.
Estimation of Secondary Flow Pressure of an Annular-Injection-Type Supersonic Ejector Using Fabri Choking
Kim Sehoon ; Kwon Sejin ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 1, 2005, Pages 61~66
A theoretical analysis is developed for an annular-injection-type supersonic ejector having a second-throat downstream the ejector under the assumption that the Fabri choking is placed in mixing chamber. Non mixing theory is applied to formulate secondary flow pressure in the region between inlet of the mixing chamber and Fabri choking. To describe the shock standing at the inlet of the mixing chamber, two dimensional oblique shock relations are used and it is assumed that the shock affects only primary flow at Fabri choking plane. Physical constraint, which is that primary flow pressure and secondary flow pressure are same at Fabri choking plane, is added. In conclusion, it agrees well with experiments in case of small contracting angle of mixing chamber, under 4degrees.
Overview on Hypersonic Scramjet Engine Developments
Won Su-Hee ; Jeung In-Seuck ; Choi Jeong-Yeol ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 1, 2005, Pages 67~83
The evolution of hypersonic scramjet engines was reviewed from the 1960s to the present. Concepts of hypersonic air-breathing propulsion systems based on scramjet engine, such as combined-cycle engine, were described and compared with other high-speed propulsion systems. The development history of scramjet engines over the past 40 years odd was introduced with priority given to the efforts in the United States, and the current status of scramjet technology was reviewed through the recent development programs in several developed countries.