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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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Journal of the Korean Society for Aeronautical & Space Sciences
Journal Basic Information
Journal DOI :
The Korean Society for Aeronautical & Space Sciences
Editor in Chief :
Volume & Issues
Volume 38, Issue 12 - Dec 2010
Volume 38, Issue 11 - Nov 2010
Volume 38, Issue 10 - Oct 2010
Volume 38, Issue 9 - Sep 2010
Volume 38, Issue 8 - Aug 2010
Volume 38, Issue 7 - Jul 2010
Volume 38, Issue 6 - Jun 2010
Volume 38, Issue 5 - May 2010
Volume 38, Issue 4 - Apr 2010
Volume 38, Issue 3 - Mar 2010
Volume 38, Issue 2 - Feb 2010
Volume 38, Issue 1 - Jan 2010
Selecting the target year
Numerical Analyses and Wind Tunnel Tests of a Propeller for the MAV Propulsion
Cho, Lee-Sang ; Lee, Sea-Wook ; Cho, Jin-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 10, 2010, Pages 955~965
DOI : 10.5139/JKSAS.2010.38.10.955
The MH-75 propeller for the MAV propulsion is designed using a free vortex design method which considers design parameters such as the hub-tip ratio, the twist angle distribution, the maximum camber location and the chord length of the propeller blade. Aerodynamic characteristics of the MH-75 propeller are predicted by changing the flight speed using the frequency domain panel method. And, the thrust characteristics of the MH-75 propeller are measured using the balance system of the subsonic wind tunnel for the validation of numerical results. The performance characteristics of the MH-75 propeller satisfied with design requirements. Numerical results of the MH-75, which are predicted by the frequency domain panel method, are more agree with experimental results compare with XFOIL.
Damping Characteristic of Helmholtz Resonator according to Its Geometry and Sound Pressure Level
Song, Jae-Kang ; Kim, Ki-Woo ; Chae, Byoung-Chan ; Ko, Young-Sung ; Kim, Sun-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 10, 2010, Pages 966~972
DOI : 10.5139/JKSAS.2010.38.10.966
Damping characteristics of a Helmholtz resonator to passively control the combustion instability were investigated by linear acoustic analysis and atmospheric acoustic tests. Its orifice length and diameter were selected as the design parameters and supplied SPL(sound pressure level) effect on damping characteristics were investigated. Damping capacity is improved by decreasing the orifice length as well as by increasing the orifice diameter. Also, the results showed that the damping capacity of the resonator decreased nonlinearly about above 110 dB and instabilities in the nonlinear region were more effectively suppressed by increasing the orifice diameter.
Non-linear Shimmy Analysis of a Nose Landing Gear with Free-play
Yi, Mi-Seon ; Hwang, Jae-Up ; Bae, Jae-Sung ; Hwang, Jae-Hyuk ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 10, 2010, Pages 973~978
DOI : 10.5139/JKSAS.2010.38.10.973
In this paper, we studied the shimmy phenomena of an aircraft nose landing gear considering free-play. Shimmy is a self-excited vibration in lateral and torsional directions of a landing gear during either the take-off or landing. This phenomena is caused by a couple of conditions such as low torsional stiffness of the strut, friction and free-play in the gear, wheel imbalance, or worn parts, and it may make an aircraft unstable. Free-play non-linearity is linearized by the described function for a stability analysis in a frequency domain, and time marching is performed using the fourth-order Runge-Kutta method. We performed the numerical simulation of the nose landing gear shimmy and investigated its linear and nonlinear characteristics. From the numerical results, we found limit-cycle-oscillations at the speed under linear shimmy speed for the case considering free-play and it can be concluded that the shimmy stability can be decreased by free-play.
Interoperability Analysis of GPS and Galileo on Time
Shin, Mi-Young ; Song, Se-Phil ; Ko, Jae-Young ; Yang, Sung-Hoon ; Lee, Sang-Jeong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 10, 2010, Pages 979~984
DOI : 10.5139/JKSAS.2010.38.10.979
The users who use a combined GPS/Galileo receiver will benefit from an improved availability of the combined system and a reduced dependence on one particular positioning system. However, these users must solve the problem of an offset between the time scales of GPS and Galileo (GGTO). GGTO must be analyzed for not only a navigation system but also a timing system requesting precise time service. This paper analyzes the interoperability problem in a combined GPS/Galileo timing receiver and estimates the timing performance under various assumptions. The GPS real measurements were collected by using the commercial timing receiver from Ashtech Ltd. and the Galileo measurements were generated by a simulation software. A suitable test scenario set-up and the performance in a point of timing stability was evaluated.
A study on the pintle-tip shapes effect of nozzle flow using cold-flow test
Kim, Joung-Keun ; Park, Jong-Ho ; Lee, Jong-Hoon ; Jeon, Min-Kyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 10, 2010, Pages 985~991
DOI : 10.5139/JKSAS.2010.38.10.985
The objective of this work was to investigate the pintle-tip shape effect on nozzle flow and thrust by cold flow test. When nozzle throat area was decreased by pintle movement, chamber pressure was increased monotonously but thrust was increased differently according to every pintle-tip shape. At the same chamber pressure and nozzle throat area, thrust of convex pintle-tip shape was mostly larger than that of concave one. Nozzle wall pressure distribution and magnitude of pintle-tip load depended on the pintle-tip shape, pintle position and nozzle throat area.
Development of a Hall-thruster Propulsion Controller for Science Technology Satellite-3
Rhee, Sung-Ho ; Cho, Hee-Keun ; Lyou, Joon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 10, 2010, Pages 992~997
DOI : 10.5139/JKSAS.2010.38.10.992
The Propulsion Control Module(PCM) of Hall-thruster Propulsion System(HPS) for Science and Technology Satellite-3 (STSAT-3) has the flow control accuracy of less than
3% and the pressure control accuracy of less than
5%. The pressure controller adjusts pressure around the set point by using a Proportional Flow Control Valve (PFCV) and a high pressure transducer, while the flow controller regulates the flow rate using PFCV and the anode current telemetry of the Hall Thruster. The controllers are chosen as the Proportional and Integral(PI) type, and the PI gains are tuned based on the Matlab simulations. The result of the PCM test had the flow control accuracy of less than
1.87% and the pressure control accuracy of less than
5%. This paper describes the design, realization, and performance test results of the PCM.
Trans Lunar Injection (TLI) Maneuver Design and Analysis using Finite Thrust
Song, Young-Joo ; Park, Sang-Young ; Kim, Hae-Dong ; Lee, Joo-Hee ; Sim, Eun-Sup ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 10, 2010, Pages 998~1011
DOI : 10.5139/JKSAS.2010.38.10.998
For preparing Korean lunar missions, an Earth-Moon transfer trajectory is designed and analyzed using finite thrust. To be a more realistic scenario, kick motor`s performance which is used for TLI (Trans Lunar Injection) maneuver is assumed to have a certain maximum capability. Under this assumption, optimal Earth-Moon transfer trajectory analysis is made from the beginning of Earth departure to the final lunar closest approach. As a results, optimal Earth-Moon transfer trajectory solutions with finite thrust are compared to those of designed with impulsive thrust in previous study. It is confirmed that if the trajectory solutions derived with impulsive burn is directly applied to estimate the finite burn trajectory solutions, careful consideration for finite burn losses must be paid as for TLI maneuver. Presented algorithm and various results will give numerous insights into the future Korea`s Lunar missions using finite thrust engines.
Design of Flight Data Processing System for Multiple Target Flight Test
Chong, Kyoung-Ho ; Oh, Se-Jin ; Bang, Hee-Jin ; Lee, Yong-Jae ; Kim, Heung-Bum ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 10, 2010, Pages 1012~1019
DOI : 10.5139/JKSAS.2010.38.10.1012
In this paper, The flight data processing system was designed for multiple target flight test. For flight data processing, multiple target grouping, data fusion processing, and data slaving processing were performed and, as a data fusion filter, centralized, and federated Kalman filters were designed. A centralized kalman filter was modified in order to improve the vehicle`s low altitude measurement using radar`s SNR and estimation process. From the testing of multiple target missile, it confirmed flight trajectory measurement was improved in low altitude area and the beginning stage of vehicle.
On-Board Black Body Thermal Design and On-Orbit Thermal Analysis for Non-Uniformity Correction of Space Imagers
Oh, Hyun-Ung ; Shin, So-Min ; Hong, Ju-Sung ; Lee, Min-Kyu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 10, 2010, Pages 1020~1025
DOI : 10.5139/JKSAS.2010.38.10.1020
On-board black body is used for radiation temperature calibration of spaceborne radiometers and imaging systems. The thermal design of black body proposed in this study is basically composed of heaters to heat-up the black body from low to high temperature during the calibration, heat pipe to transfer residual heat on the black body just after calibration to radiator on the S/C and heaters on the radiator to keep the certain temperature range of the black body during non-calibration. In the present work, the effectiveness of thermal design of on-board black body has been investigated by on-orbit thermal analysis.
Development of BLDC Motor Driven Cryogenic Thrust Control Valve for Liquid Propellant Rocket Engine
Jung, Tae-Kyu ; Lee, Soo-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 10, 2010, Pages 1026~1030
DOI : 10.5139/JKSAS.2010.38.10.1026
This paper summarizes the activities performed for the development of a BLDC(Brushless Direct Current) motor driven cryogenic thrust control valve with application to KSLV-II rocket engine. The developed thrust control valve can modulate the flow rate of liquid oxygen under cryogenic temperature of 90K and high pressure of 113.2 bar with the help of electro-mechanical actuator driven by a BLDC motor. This valve can be applied to an engine combustion test after minor change because all development certification test have been performed successfully.
Lightweight Metallic Bipolar Plates of PEMFC for a Small Reconnaissance UAV
Kim, Ki-In ; Lee, Jong-Kwang ; Jang, Bo-Sun ; Kwon, Se-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 10, 2010, Pages 1031~1037
DOI : 10.5139/JKSAS.2010.38.10.1031
This paper proposed lightweight aluminum bipolar plates as an alternative for conventional graphite bipolar plates in fuel cell systems used as a power source for small reconnaissance UAVs. Since bipolar plates occupy more than 80% of the total weight of the fuel cell system, lightweight aluminum bipolar plates can improve the overall payload and flight time of the fuel cell UAV. The aluminum and graphite bipolar plates were fabricated to compare the performance of each of them. A 15% higher performance per weight was obtained from aluminum bipolar plates than the graphite bipolar plates. Also, the performance of a single cell using aluminum bipolar plates was evaluated under various operating conditions.
Radiation Exposure of an Astronaut subject to Various Space Radiation Environments and Shielding Conditions
Chae, Myeong-Seon ; Chung, Bum-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 10, 2010, Pages 1038~1048
DOI : 10.5139/JKSAS.2010.38.10.1038
Radiation exposures of an astronaut during the space travels to the International Space Station(ISS) of the Soyuz and the Moon of the Apollo, were calculated considering the altitude, boarding time, period of stay, kinds of spaceships and space suits. The calculated radiation exposures decrease dramatically according to the thickness of the shielding by the wall of the spaceships and by the space suits. For the space travel to the ISS of Soyuz at Low Earth orbit, the thickness of the spaceship required to optimally reduce the radiation exposure is 3 cm. For the Extravehicle Mobility Unit(EMU) the exposures are minimized at 4 cm of the aluminized Mylar and 5 cm of the Demron, respectively. The aluminized Mylar showed better radiation shielding than the Demron which contains the high Z materials. The radiation exposures of an astronaut were
Sv for the ISS travel and
Sv for the Moon explore. The high concentration of the high energy proton flux at the surface of the Moon results in high radiation exposure. The calculation scheme and results of this study can be used in the design of the shielding performance of a spaceship and space suits.