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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
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Volume & Issues
Volume 39, Issue 12 - Dec 2011
Volume 39, Issue 11 - Nov 2011
Volume 39, Issue 10 - Oct 2011
Volume 39, Issue 9 - Sep 2011
Volume 39, Issue 8 - Aug 2011
Volume 39, Issue 7 - Jul 2011
Volume 39, Issue 6 - Jun 2011
Volume 39, Issue 5 - May 2011
Volume 39, Issue 4 - Apr 2011
Volume 39, Issue 3 - Mar 2011
Volume 39, Issue 2 - Feb 2011
Volume 39, Issue 1 - Jan 2011
Selecting the target year
Aerodynamic Characteristics of a Three-Dimensional Wing in Heave Oscillation
Chin, Chul-Soo ; Kim, Tae-Wan ; Lee, Hyoung-Wook ; Han, Cheol-Heui ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 10, 2011, Pages 905~911
DOI : 10.5139/JKSAS.2011.39.10.905
With the progress of micro actuator technology, studies on the development of micro air flapping wing vehicles are actively undergoing. In the present study, the changes of both lift and thrust characteristics of the wings are investigated using a boundary element method. Lift of the heaving wing is not generated when the wing is beating with smaller frequencies than 1 Hz. Thrust increases with amplitude and frequency. As the wing`s taper and aspect ratios increase, both lift and thrust also increase. Results on the pitching oscillation and flapping motion will be included in the future work.
An Experimental Study on Roll-Damping Characteristics of a Spinning Projectile at High Speed Region
Oh, Se-Yoon ; Lee, Do-Kwan ; Kim, Sung-Cheol ; Kim, Sang-Ho ; Ahn, Seung-Ki ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 10, 2011, Pages 912~918
DOI : 10.5139/JKSAS.2011.39.10.912
The purpose of this research is to determine the dynamic roll-damping data of a spinning projectile in wind-tunnel testing. In the present work, the high-speed wind-tunnel tests for the roll-damping measurements were conducted on a spin-stabilized projectile model in the Agency for Defense Development`s Tri-Sonic Wind Tunnel at spin rates about 12,000 rpm. The test Mach numbers ranged from 0.7 to 1.05, and the angles of attack ranged from -4 to +10 deg. The validity of the wind-tunnel measurement techniques was evaluated by comparing them with the previous test results on the same configuration.
The effect of Local Vibration Modes on the Flutter
Shin, Young-Sug ; Kim, Heon-Ju ; Kim, Seong-Tae ; Kim, Jae-Young ; Hwang, Chul-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 10, 2011, Pages 919~926
DOI : 10.5139/JKSAS.2011.39.10.919
The fin of high speed air vehicle is composed of skins and strong skeletons. In the flutter analysis, the eigenmodes of a fin are used for evaluating the unsteady aerodynamic force and the modal approach is applied for solving the flutter equation in both time and frequency domain. Therefore, the proper eigenmodes used for a modal flutter analysis should be chosen. For the appropriate choice of eigenmodes, when there exist local modes of a skin in the high modes, the effects of those modes on the unsteady aerodynamic force and flutter characteristics are anlalyzed.
Design Parameter Analysis of a Solar-Powered, Potential Energy-Storing, Long Endurance UAV
Yang, In-Young ; Lee, Bo-Hwa ; Chang, Byung-Hee ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 10, 2011, Pages 927~934
DOI : 10.5139/JKSAS.2011.39.10.927
Design parameter analysis is performed for a solar-powered UAV, storing potential energy by climb flight. Parameters related to the flight for saving potential energy, i.e. minimum & maximum altitudes for level flight, gliding & climbing angle, design point speed & altitude, gliding & climbing start time are investigated as design parameters. Weight and size of the UAV are determined using a weight model for the components of the solar-powered UAVs. Produced energy and consumed energy are calculated using these weight and size, yielding the required weight of the battery for a given mission. Relationship between the total weight of the UAV and each parameter is investigated. For the parameters listed above, there exist their ranges only where the design is possible. And there exist optimal values of these parameters minimizing the total weight.
Satellite Attitude Control using Reaction Wheels and CMGs
Son, Jun-Won ; Rhee, Seung-Wu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 10, 2011, Pages 935~945
DOI : 10.5139/JKSAS.2011.39.10.935
We study X-axis or Y-axis high agile attitude control method, using four reaction wheels and two control moment gyros. Since normal satellites use same actuators, researchers design an attitude controller first, and then allocate torque commands to each actuator. However, our satellite uses both control moment gyros and reaction wheels, whose torque output differences are very large. Therefore, we cannot apply normal attitude controller design procedure. In this paper, we solve this problem by combining actuator torque command and attitude controller. Through numerical simulations, we show that our method enables satellite high agility.
Analysis of GBAS Availability and Requirement with respected to Protection Level at Jeju International Airport
Ahn, Jong-Sun ; Won, Dae-Hee ; Sung, San-Kyung ; Heo, Moon-Beom ; Lee, Eun-Sung ; Lee, Young-Jae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 10, 2011, Pages 946~951
DOI : 10.5139/JKSAS.2011.39.10.946
This paper presents the simulation results of GBAS availability and requirement (with respected to Vertical Protection Level) using simulated data at CAT I, CAT II/III DH point (Decision Height), which are generated using Jeju international GNSS reference position, aircraft horizontal velocity and reference/aircraft GNSS antenna performance index and so on. Two kinds of protection levels are presented, one is from a hypothesis (H0) and other is from a alternative hypothesis (H1). These protection levels are compared with AL (Alert Limit), and we analyse the GBAS availability and requirement for CAT I and CAT II/III at the airport.
Mechanical Stability Analysis of PCB and Component for Launch and On-orbit Environment based on Fatigue Failure Theory and FEM
Jeong, Suk-Yong ; Oh, Hyun-Ung ; Lee, Kyung-Joo ; Kim, Byoung-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 10, 2011, Pages 952~958
DOI : 10.5139/JKSAS.2011.39.10.952
On-board IR calibration device has been developed for calibration of spaceborne image sensor. It is composed of a blackbody to provide two different radiance temperatures, tilt mirror with a function of stow and deploy to view the blackbody during the calibration and on-board calibration control unit to control the function of the blackbody and tilt mirror. In this paper, to guarantee the structural safety of the unit, the structural and thermal analysis including a thermo-elastic analysis for verifying structural safety on the soldered part of chips have been performed. In addition, safety margin of the chips on the PCB obtained from the conventional analytical method has been compared to the results from the FEM analysis.
A Electric Power Source Modeling and Simulation for Electric Propulsion Systems of a Fuel Cell Powered Small UAV
Lee, Bo-Hwa ; Park, Poo-Min ; Kim, Chun-Taek ; Kim, Sung-Yug ; Yang, Soo-Seok ; Ahn, Seok-Min ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 10, 2011, Pages 959~965
DOI : 10.5139/JKSAS.2011.39.10.959
A modeling and power simulation of a small UAV`s electric propulsion systems is described. Each power source is modeled and simulated in Matlab/Simulink and it is compared flight test data during 4 hr 30 min with simulation results about 200 W electric propulsion system using fuel cell and battery as a main power sources. In result, it is properly simulated performance and dynamic characteristic of each electric power source. Through this, it is revealed that the simulation is available as a means of predicting power characteristic variation for electric propulsion systems of different class.
Research Activities of Transpiration Cooling for High-Performance Flight Engines
Hwang, Ki-Young ; Kim, You-Il ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 10, 2011, Pages 966~978
DOI : 10.5139/JKSAS.2011.39.10.966
Transpiration cooling is the most effective cooling technique for the high-performance liquid rockets and air-breathing engines operating in aggressive environments with higher pressures and temperatures. When applying transpiration cooling, combustor liners and turbine blades/vanes are cooled by the coolant(air or fuel) passing through their porous walls and also the exit coolant acting as an insulating film. Practical implementation of the cooling technique has been hampered by the limitations of available porous materials. But advances in metal-joining techniques have led to the development of multi-laminate porous structures such as Lamilloy
fabricated from several diffusion-bonded, etched metal thin sheets. And also with the availability of lightweight, ceramic matrix composites(CMC), transpiration cooling now seems to be a promising technique for high-performance engine cooling. This paper reviews recent research activities of transpiration cooling and its applications to gas turbines, liquid rockets, and the engines for hypersonic vehicles.
Development of Embedded Program for UAV Flight Control System using RTOS and Model-Based Auto Code Generation
Kim, Sung-Hwan ; Cho, Sang-Ook ; Kim, Sung-Su ; Ryoo, Chang-Kyung ; Choi, Kee-Young ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 10, 2011, Pages 979~986
DOI : 10.5139/JKSAS.2011.39.10.979
In this paper, an embedded program of a flight control system for a small high performance UAV is introduced. The program consists of modules for device management and guidance and control. The device management system handles navigation sensors and mission equipments. The program for the guidance and control system is used to accomplish various kinds of missions and realize automation of flight control. Driver programs embedded in the device management system for operation of sensors and external devices are based on Texas Instrument`s DSP/BIOS RTOS(realtime operating system). The on-board programs for the guidance and control system is obtained by using the model-based auto code generation technology.
An efficient Method of Antenna Placement considering EMI between equipments on UAV
Kim, Choon-Won ; Kim, Ji-Hoon ; Kwon, Kyoung-Il ; Chung, Deok-Cho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 10, 2011, Pages 987~994
DOI : 10.5139/JKSAS.2011.39.10.987
This paper presents An efficient method of antenna placement considering EMI(Electromagnetic Interference) between equipments which are mounted on the UAV(Unmanned Air Vehicle). The analysis is accomplished for voice communication radio, control datalink, TCAS(Traffic Alert Collision & Avoidance System) and GPS(Global Positioning System) which are vulnerable to EMI because the frequencies are close to each other. There are two steps for analysis procedure : The first one is selecting antenna position on the UAV by monitoring return loss and pattern variation of each antenna. The second one is analyzing EMI via antennas between equipments. In the EMI analysis, spurious level of each transmitter, coupling level between antennas and system noise property are considered. This procedure can be used to predict EMI between equipments in development stage.