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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 19, Issue 6 - Dec 2015
Volume 19, Issue 5 - Oct 2015
Volume 19, Issue 4 - Aug 2015
Volume 19, Issue 3 - Jun 2015
Volume 19, Issue 2 - Apr 2015
Volume 19, Issue 1 - Feb 2015
Selecting the target year
Fabrication Method and Performance Evaluation of Micro Igniter for MEMS Thruster
Lee, Jongkwang ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 1, 2015, Pages 1~8
DOI : 10.6108/KSPE.2015.19.1.001
Micro igniter on the glass membrane for MEMS thruster was developed. The stability of the micro igniter by using a glass membrane with a thickness of tens of microns was improved. The micro igniter was fabricated by anisotropic wet etching of photosensitive glass and deposition of Pt/Ti for electric heat coil. The solid propellant was loaded into the propellant chamber without an especial technique due to the high structural stability of the glass membrane. Ignition tests were performed successfully. The minimum ignition delay was 27.5 ms with an ignition energy of 19.3 mJ.
A Study on the Effect of Mid Layer on Supersonic 2D Double Shear Layer
Kim, Dongmin ; Baek, Seungwook ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 1, 2015, Pages 9~17
DOI : 10.6108/KSPE.2015.19.1.009
The basic flow configuration is composed of a plane, double shear layer where relatively thin mid gas layer is sandwiched between air and fuel stream. The present study describes numerical investigations concerning the combustion enhancement according to a variation of mid layer thickness. In this case, the effect of heat release in turbulent mixing layers is important. For the numerical solution, a fully conservative unsteady
order time accurate sub-iteration method and
order TVD scheme are used with the finite volume method including k-
SST model. The results consists of three categories; single shear layer consists of fuel and air, inert gas sandwiched between fuel and air, cold fuel gas sandwiched between fuel and air. The numerical calculations has been carried out in case of 1, 2, 4 mm of mid layer thickness. The height of total gas stream is 4 cm. The combustion region is broadened in case of inert gas layer of 2, 4 mm thickness and cold fuel layer of 4 mm thickness compared with single shear layer.
Boron-Containing Solid Fuel Combustion and Cycle Analysis
Lee, Tae Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 1, 2015, Pages 18~24
DOI : 10.6108/KSPE.2015.19.1.018
An experimental investigation was conducted to figure out the effects of the inlet air temperature on the combustion efficiency using the fuel grains which were highly loaded with boron carbide. The results showed that the normalized combustion efficiency increased with the inlet air temperature, apparently the result of enhanced combustion of the boron particles. Even though the combustion efficiency is increased, the overall efficiency through the semi-empirical method, is decreased with the increasing inlet air temperature. Brayton cycle analysis has been performed using the heat input parameter and combustor Mach number, those two parameters are important role for the performance and similar trends are shown at the experimental results.
Aerodynamic Drag Reduction in Cylindrical Model Using DBD Plasma Actuator
Lee, Changwook ; Sim, Ju-Hyeong ; Han, Sunghyun ; Yun, Su Hwan ; Kim, Taegyu ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 1, 2015, Pages 25~32
DOI : 10.6108/KSPE.2015.19.1.025
Dielectric barrier discharge (DBD) plasma actuator was designed to reduce aerodynamic drag in a cylindrical model and wind tunnel test was performed at various wind velocities. In addition, computational fluid dynamics (CFD) analysis and flow visualization were used to investigate the effect of the plasma on the flow stream in the cylinderical model. At low wind velocity, the plasma actuator had no effects because flow separation did not appear. The aerodynamic drag was reduced by 14% at 14 m/s and by 27% at 17 m/s, respectively. It was confirmed by CFD analysis and flow visualization that the DBD plasma actuator decreased in pressure difference around the cylindrical model, thus decreasing the magnitude of wake vortex.
Kinetic Analysis of Energetic Materials Using Differential Scanning Calorimetry
Kim, Yoocheon ; Park, Jungsoo ; Yang, Seungho ; Park, Honglae ; Yoh, Jai-Ick ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 1, 2015, Pages 33~41
DOI : 10.6108/KSPE.2015.19.1.033
The kinetic analysis of energetic materials using Differential Scanning Calorimetry (DSC) is proposed. Friedman Isoconversional method is applied to DSC experiment data and AKTS software is used for analysis. The proposed kinetic scheme has considerable advantage over the standard method based on One-Dimenaionl Time to Explosion (ODTX). Reaction rate and product mass fraction simulation are conducted to validate extracted kinetic scheme. Also a slow cook-off simulation is implemented on
for validating the applicability of the extracted kinetics scheme to a practical thermal experiment.
LES Investigation of Pressure Oscillation in Solid Rocket Motor by an Inhibitor
Hong, Ji-Seok ; Moon, Hee-Jang ; Sung, Hong-Gye ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 1, 2015, Pages 42~49
DOI : 10.6108/KSPE.2015.19.1.042
The pressure oscillation induced by inhibitor in a solid rocket motor has been investigated by 3D large eddy simulation(LES) and proper orthogonal decomposition(POD). The vortex generation and breakdown at inhibitor are periodically observed between the inhibitor and the nozzle by flow-acoustic coupling mechanism. The excitation of pressure oscillation occurs as the flow impinges on the submerged nozzle head which recirculate in the cavity in rear dome of the motor chamber. The vortex generation frequency is closely related with the shedding frequencies of the detached vorticities at the inhibiter, which fairly compared with the experimental data.
A Development Trend Study of Bipropellant Rocket Engine for Orbit Transfer and Attitude Control of Satellite
Jang, Yo Han ; Lee, Kyun Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 1, 2015, Pages 50~60
DOI : 10.6108/KSPE.2015.19.1.050
A propulsion system of a satellite provides a necessary thrust to reach to the final orbit after a separation from a launch vehicle. Also, it supplies pulse moments to maintain the satellite in a mission orbit and for its attitude controls during a mission life time. The present study investigates the development trend of bipropellant rocket engines for an orbit transfer and an attitude control of a satellite using monomethylhydrazine and hydrazine for fuel and dinitrogen tetroxide for oxidizer to derive fundamental specifications which are necessary for domestic development researches. Also, their major performance characteristics are summarized.
1-D Analysis for Water Spray Cooling of Exhaust Gas in Combustor Test Facility
Im, Ju Hyun ; Kim, Myung Ho ; Kim, Yeong Ryeon ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 1, 2015, Pages 61~67
DOI : 10.6108/KSPE.2015.19.1.061
The cooling of hot exhaust gas is an important issue for the construction of combustor test facility. Water spray is an effective method for exhaust gas cooling due to its large latent heat in process of evaporation. In this study, 1-D analysis has been performed based on continuity, energy conservation, and saturated vapor property to understand water spray cooling of combustion gas. In the exhaust duct of combustor test facility, the injected water decreases combustion gas temperature, and evaporates in the combustion gas. However, some of the injected water is collected in the sump due to condensation. The evaporation of water helps combustion gas cooling, but causes pressure increase inside the exhaust duct due to increase of vapor pressure. These phenomena has been analyzed by 1-D modeling in this study. From 1-D analysis, the adequate mass flow rate of water spray to cool combustion gas and to avoid excessive pressure rise inside the exhaust duct has been decided.
Analysis of Unsteady Combustion Performance in Solid Rocket Motor with Pintle
Ki, Taeseok ; Ha, Dongsung ; Jin, Jungkun ; Lee, Hosung ; Yoon, Hyungull ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 1, 2015, Pages 68~75
DOI : 10.6108/KSPE.2015.19.1.068
In this paper, unsteady characteristics of pressure in solid rocket motor were analyzed by using response of pintle actuation, pressure and thrust data from ground test. Pressure and thrust in solid rocket motor can be controlled in real time by varying nozzle throat area with pintle, installed in the valve. Unsteady characteristics of pressure can be observed in this system occurred by various reasons. Two critical reasons, error of pintle actuation and ablation of center tube, are found and effects of each reason can be analyzed individually by re-prediction of pressure with response of pintle actuation and analyzing thrust to pressure ratio.
Basic Design of Propellant Ground Support Equipment and Flame Deflector for KSLV-II Launch Complex
Kang, Sunil ; Oh, Hwayoung ; Kim, Daerae ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 1, 2015, Pages 76~86
DOI : 10.6108/KSPE.2015.19.1.076
KSLV-II, a new launch vehicle of Korea, requires a new launch complex(LC) for its own and proper launch operations. The new launch complex will be constructed in NARO Space Center neighboring KSLV-I launch complex for maximizing operation efficiency and economic matters. The launch complex consists of three ground support equipments, i.e., mechanical, electrical, and fuel in general. The fuel ground support equipment could be defined as a combination of systems for storage and supply of propellants and gases which are required by a launch vehicle. The compositions, functions and capabilities of fuel ground support equipment are introduced in this paper. In addition, basic design results of flame deflector configurations are included.
Development Trend of Cold Gas Propulsion System of a Simulator for Maneuvering and Attitude Control Design Verification of Spacecraft
Kim, Jae-Hoon ; Lee, Kyun Ho ; Hong, Sung Kyung ; Kim, Hae-Dong ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 1, 2015, Pages 87~97
DOI : 10.6108/KSPE.2015.19.1.087
In general, such ground based methods are utilized to validate maneuvering and attitude control logics of a spacecraft by a simulation with a flight software at a design phase and a integrated function test with actual hardwares at a system level. Recently, varification researches using operating simulators are getting increase using compact and precise components under a ground condition. The present paper investigates and summarized the development trend of cold gas propulsion systems for the spacecraft simulators and their major performance characteristics to derive fundamental data which are necessary for a conceptual design of the simulator.
Conceptual Design of Cold Gas Propulsion System of a Ground Simulator for Maneuver and Attitude Control Design Verification of Spacecraft
Kim, Jae-Hoon ; Lee, Kyun Ho ; Hong, Sung Kyung ; Kim, Hae-Dong ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 1, 2015, Pages 98~110
DOI : 10.6108/KSPE.2015.19.1.098
Recently, a validation research of maneuvering and attitude control logics of a spacecraft under a ground condition is getting increase by using operating simulators with compact and precise components. For that, a cold gas propulsion system is generally used for maneuvering and attitude control of spacecraft ground simulators for its simplicity and a high reliability. In the present study, major design parameters of a cold gas propulsion system are derived to meet mission requirements based on conceptual design results of a simulator. And additionally, commercial components with proper specifications are selected for system assembly.