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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
Nonlinear Stability Analysis of Boundary Layers by using Nonlinear Parabolized Stabiltiy Equations
Park, Dong-Hun ; Park, Seung-O ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 9, 2011, Pages 805~815
DOI : 10.5139/JKSAS.2011.39.9.805
Nonlinear Parabolized Stability Equations(NSPE) can be effectively used to study more throughly the transition process. NPSE can efficiently analyze the stability of a nonlinear region in transition process with low computational cost compared to Direct Numerical Simulation(DNS). In this study, NPSE in general coordinate system is formulated and a computer code to solve numerically the equations is developed. Benchmark problems for incompressible and compressible boundary layers over a flat plate are analyzed to validate the present code. It is confirmed that the NPSE methodology constructed in this study is an efficient and effective tool for nonlinear stability analysis.
The Calculation of Propeller Thrust using Semi-infinite Helical Vortices and a Wind tunnel Test
Park, Young-Min ; Kim, Beom-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 9, 2011, Pages 816~822
DOI : 10.5139/JKSAS.2011.39.9.816
In this study, a program has been coded to evaluate propeller thrust rapidly following the effects of propeller shapes and the environmental facts. At this time, Semi-infinite Helical Vortices model is used to predict the induction factor which is introduced by Kawada. This program is based on Wrench's Propeller lifting line theory, and it can predict aerodynamic coefficients such as thrust, power, and efficiency. First of all, this program is compared with test results of NACA reports to verify of the reliability. Secondly, subsonic wind tunnel test has been performed following variations of propeller's rpm and inflow velocities.
The Prediction of Aeroelasticity of F-5 Aircraft's Horizontal Tail with Various Shape of External Stores
Lee, Ki-Du ; Lee, Young-Shin ; Lee, Dae-Yearl ; Kim, In-Woo ; Lee, In-Won ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 9, 2011, Pages 823~831
DOI : 10.5139/JKSAS.2011.39.9.823
According to the development of loading equipments, it is usual to change or replace the existing stores. It has been known that pylon-mounted under stores strongly affect aircraft dynamics characteristics due to the change of aerodynamics. To predict the aerodynamics and aero-elasticity is essentially requested with considering the configuration and shape of external stores during the development of aircraft and/or external stores. In this paper, computational fluid dynamics and computational structure dynamics interaction methodology are applied for prediction of aerodynamic characteristics for F-5 aircraft's horizontal tail with various shape of external stores. FLUENT and ABAQUS were used to calculate fluid and structural dynamics. Code-bridge was made base on the globally supported radial basis function to execute interpolation and mapping. As a result, even though the aeroelasticity of the horizontal tail slightly changes according to the shape of external store, the flutter was not occurred at the considered flight conditions in this study.
Study on Damping Coefficient of Shock Absorber with Magnetic Effects
Yi, Mi-Seon ; Bae, Jae-Sung ; Hwang, Jae-Hyuk ; Hwang, Do-Sun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 9, 2011, Pages 832~838
DOI : 10.5139/JKSAS.2011.39.9.832
The shock absorber with magnetic effect is suggested for a lunar lander. The shock absorber consists of a metal tube, a piston rod, and several permanent magnets moved by a piston rod in the tube, and the shock energy can be dispersed and dissipated by magnetic effects such as the magnetic force existed between a metal and magnets and the eddy current effect generated by a relative motion with a conductor and magnets. Besides, the shock-absorbing effect similar to that of a coil spring can be obtained by arranging the magnets in line, which are facing the same polar each other. The device has a very simple structure and is usable in space due to the unnecessariness of any oil or gas. The shock absorber was designed and manufactured for experiments and its spring and damping characteristics were studied by the theoretical, analytical and experimental methods.
A Guidance Law to Maintain Ballistic Trajectory for Smart Munitions
Park, Woo-Sung ; Ryoo, Chang-Kyung ; Kim, Yong-Ho ; Kim, Jong-Ju ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 9, 2011, Pages 839~847
DOI : 10.5139/JKSAS.2011.39.9.839
This paper proposes a new guidance law for increasing the lethality of munitions. The well known PNG (Proportional Navigation Guidance) is inadequate for the munitions because of some weaknesses. Even if the munition does not have the impact point error, the acceleration command is non zero because the line-of-sight changes at all times in flight. Therefore, we use a difference between a target and an impact point. This proposed guidance law is similar to PNG in the form, but this guidance law concentrates a correction rate of flight path angle instead of the LOS (Line of Sight) rate. The correction of flight path angle is defined as the amount of impact point error. This impact point error can be calculated by neural networks rapidly. Finally, we show that the simulation results prove the suitability of this law.
Track-Before-Detect Algorithm for Multiple Target Detection
Won, Dae-Yeon ; Shim, Sang-Wook ; Kim, Keum-Seong ; Tahk, Min-Jea ; Seong, Kie-Jeong ; Kim, Eung-Tai ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 9, 2011, Pages 848~857
DOI : 10.5139/JKSAS.2011.39.9.848
Vision-based collision avoidance system for air traffic management requires a excellent multiple target detection algorithm under low signal-to-noise ratio (SNR) levels. The track-before-detect (TBD) approaches have significant applications such as detection of small and dim targets from an image sequence. In this paper, two detection algorithms with the TBD approaches are proposed to satisfy the multiple target detection requirements. The first algorithm, based on a dynamic programming approach, is designed to classify multiple targets by using a k-means clustering algorithm. In the second approach, a hidden Markov model (HMM) is slightly modified for detecting multiple targets sequentially. Both of the proposed approaches are used in numerical simulations with variations in target appearance properties to provide satisfactory performance as multiple target detection methods.
Characteristic of Hydrogen Generation from Solid-State NaBH
and Fuel Cell Operation for Fuel Cell Aircraft
Lee, Chung-Jun ; Kim, Tae-Gyu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 9, 2011, Pages 858~865
DOI : 10.5139/JKSAS.2011.39.9.858
This paper describes the characteristics of hydrogen generation from solid-state
and fuel cell operation for fuel cell aircraft. The solid-state
was used for a high hydrogen storage density, and was reacted with hydrochloric acid to generate hydrogen. The hydrogen generation rate for the solid-state
reaction was measured at various conditions. As a result, the hydrogen generation rate was increased with the feed rate and concentration of hydrochloric acid, while not be affected by the reaction temperature. A fuel cell was connected with the solid-state
hydrogen generator. The stable power output was obtained at the gradual and sudden increases of electric loads.
A Study of Wind Tunnel Test of a Korean Traditional Bangpae Kite with the Wind Hole and Spanwise Curved Dihedral
Kang, Chi-Hang ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 9, 2011, Pages 866~870
DOI : 10.5139/JKSAS.2011.39.9.866
In this paper, the aerodynamic forces of a Korean Traditional Bangpae Kite with the wind hole and spanwise curved dihedral were measured by wind tunnel test. For the flat plate kite without the wind hole, the stall presents at
=1.2. The Korean Traditional Bangpae Kite with the wind hole had
without the apparent stall phenomena. As the wind hole size growing, the lift and drag of kite were changed slowly after stalling angle of attack. As increasing the leading edge dihedral angle, lift curves were more increased than drag curves. As the growing of wind hole size, the effect of dihedral angle was constant affect to the lift and drag of kite.
A Study on Trim Flight Condition for a Korean Traditional Bangpae Kite with Low Aspect Ratio
Kang, Chi-Hang ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 9, 2011, Pages 871~876
DOI : 10.5139/JKSAS.2011.39.9.871
In this paper, the equilibrium flight conditions of a Korean Traditional Bangpae Kite with low aspect ratio were analyzed by it's aerodynamic data of wind tunnel test. The data of aerodynamic forces and center of pressure of the Kite were used to calculate the relative length of bridles to satisfy the condition of settling the kite to the static equilibrium steady state between
. From this equilibrium flight performance analysis, we obtained (
)c of the rear bridle length corresponding to 0.88c of fixed front bridle length. These results were exact agreement with the relative bridle lengths by Korean classical method.
Measurement of Thermal Deformation of a Double Ring Structure using Digital Image Correlation Technique
Jin, Tailie ; Goo, Nam-Seo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 9, 2011, Pages 877~882
DOI : 10.5139/JKSAS.2011.39.9.877
In this paper, thermal deformation of a double ring structure using digital image correlation technique (DIC) was measured. The double ring structure consisted of two parts; the inner ring was aluminium which had a large thermal expansion coefficient and the outer ring was titanium which had a small thermal expansion coefficient. We heated the double ring structure from
in a chamber and at the same time, two cameras captured surface images of the double ring structure. Initially, there was a 21
gap between the inner ring and outer ring. The gap was closed at around
and after that, two rings expanded together. In order to compare the experimental results with analysis results, a finite element analysis was performed using ANSYS. The results of DIC measurement and ANSYS analysis were compared and agreed well.
Test of UAV Tracking Antenna System Using Kalman Filter Based on GPS Velocity and Acceleration
Seo, Young-Jun ; Lee, Dae-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 9, 2011, Pages 883~888
DOI : 10.5139/JKSAS.2011.39.9.883
The UAV tracking antenna system based on GPS has a characteristic of update of position information which can occurs a position error. To reduce the position error, UAV tracking antenna system separates period of GPS update-rate and predicts the position of UAV using divided time points. These process improves the tracking performance of UAV. To predict the position of UAV by divided time points, we used a linear kalman filter based on the velocity and acceleration. Using this system, we measured velocity and acceleration according to the change of position. Finally, we can predict the change of position on divided time points.
Source Localization Technique for Radar Pulse Emission by Using Scanning Method of Interest Area
Choi, Kyong-Sik ; Kim, Jong-Pil ; Won, Hyeon-Kwon ; Park, Jae-Hyun ; Kim, In-Gyu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 9, 2011, Pages 889~895
DOI : 10.5139/JKSAS.2011.39.9.889
In recent days, some techniques to prevent from radar detection have been applied on aircraft system. RWR(Radar Warning Receiver) can be used for estimating the source location of the aircraft which emits radar pulse. Current existing method of localizing radar pulse emission source is using AOA(Angle Of Arrival) and most techniques are focused on finding exact AOA to find exact location. In this case, however, the exact AOA does not always result in finding exact source location while target aircraft is moving fast. In this paper, a localization method using the phase delay of the radar pulse's low frequency applies and so a scanning method for the interest area does in order to estimate exact source location by using phase delay.
A Co-design Method for JPEG2000 Video Compression System in Telemetry using DSP and FPGA
Yu, Jae-Taeg ; Hyun, Myung-Han ; Nam, Ju-Hun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 9, 2011, Pages 896~903
DOI : 10.5139/JKSAS.2011.39.9.896
In this paper, a co-design method for JPEG2000 video compression system using DSP and FPGA is presented. By profiling the complexity of JPEG2000 algorithm, it is noticed that a MQ-coder is the most complex part. Thus, we implement the MQ-coder on FPGA for the parallel processing using VHDL to reduce the complexity. In order to verify the performance of the MQ-coder, JBIG2 standard test vector and images are used. The experimental results show that the proposed MQ-coder enhances the processing time approximately 3 times compared with the previous software MQ-coder.