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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 40, Issue 12 - Dec 2012
Volume 40, Issue 11 - Nov 2012
Volume 40, Issue 10 - Oct 2012
Volume 40, Issue 9 - Sep 2012
Volume 40, Issue 8 - Aug 2012
Volume 40, Issue 7 - Jul 2012
Volume 40, Issue 6 - Jun 2012
Volume 40, Issue 5 - May 2012
Volume 40, Issue 4 - Apr 2012
Volume 40, Issue 3 - Mar 2012
Volume 40, Issue 2 - Feb 2012
Volume 40, Issue 1 - Jan 2012
Selecting the target year
Comparison between Wilcox к - ω turbulence models for supersonic flows
Kim, Min-Ha ; Parent, Bernard ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 5, 2012, Pages 375~384
DOI : 10.5139/JKSAS.2012.40.5.375
This paper presents numerical results comparing the performance of the 2008 Wilcox
turbulence model to the one of the 1988 Wilcox
model for supersonic flows. A comparison with experimental data is offered for a shock wave/turbulent boundary layer interaction case and two ramp injector mixing cases. Furthermore, a comparison is performed with empirical correlations on the basis of skin friction for flow over a flat plate and shear layer growth for a free shear layer. It is found that the maximum injectant mass fraction of some ramp injector cases is better predicted using the 1988 Wilcox model. On the other hand, the 2008 model performs better in simulating shock-boundary layer cases.
Estimation of Aircraft Stability Derivatives Using a Subsonic-supersonic Panel Method
Gong, Hyo-Joon ; Lee, Hyung-Ro ; Kim, Beom-Soo ; Lee, Seung-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 5, 2012, Pages 385~394
DOI : 10.5139/JKSAS.2012.40.5.385
A computer program that can estimate static, dynamic stability and control derivatives using a subsonic-supersonic panel method is developed. The panel method uses subsonic-supersonic source and elementary horse shoe vortex distributions, and their strengths are determined by solving the boundary condition approximated with a thin body assumption. In addition, quasi-steady analysis on the body fixed coordinate system allows the estimation of damping coefficients of aircraft 3 axes. The code is validated by comparing the neutral point, roll and pitch damping of delta wings with published analysis results. Finally, the static, dynamic stability and control derivatives of F-18 are compared with experimental data as well as other numerical results to show the accuracy and the usefulness of the code.
Prediction of Pitch and Roll Dynamic Derivatives for Flight Vehicle using CFD
Lee, Hyung-Ro ; Gong, Hyo-Joon ; Kim, Beom-Soo ; Lee, Seung-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 5, 2012, Pages 395~404
DOI : 10.5139/JKSAS.2012.40.5.395
This paper presents computations of the dynamic derivatives of three dimensional flight vehicle configurations using CFD. The pitch dynamic derivatives are computed from the pitch sinusoidal motion, while the roll damping is computed based on steady state calculation using a non-inertial frame method. The Basic Finner and the SDM(Standard Dynamic Model) are chosen for the benchmark tests against other numerical and experimental results. For the flow calculations, a 3-D Euler solver that can be run both on the non-inertial frame and on the inertial frame is developed. A dual-time stepping method is applied for the unsteady time accurate simulations. A good agreement of pitch-roll dynamic derivatives with previously published numerical results and the experimental results is observed.
Flow Control on Wind Turbine Airfoil with a Vortex Cell
Kang, Seung-Hee ; Kim, Hye-Ung ; Ryu, Ki-Wahn ; Lee, Jun-Shin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 5, 2012, Pages 405~412
DOI : 10.5139/JKSAS.2012.40.5.405
A flow control on airfoil installed a vortex cell for high efficiency wind turbine blade in stationary and dynamic stall conditions have been numerically investigated by solving the compressible Navier-Stokes equations. The numerical scheme is based on a node-based finite-volume method with Roe`s flux-difference splitting and an implicit time-integration method coupled with dual time step sub-iteration. The computed result for the airfoil in the stationary showed that lift-drag ratio increases due to low pressure by the vortex cell. The oscillating airfoil with the vortex cell showed that the magnitude of hysteresis loop is reduced due to the enhanced vortex in the cell.
Experimental Study on the Aerodynamic Characteristics of the Ducted fan for the Propulsion of a Small UAV
Ryu, Min-Hyoung ; Cho, Lee-Sang ; Cho, Jin-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 5, 2012, Pages 413~422
DOI : 10.5139/JKSAS.2012.40.5.413
The ducted fan for a small UAV propulsion can reconnoiter and observe in a town and a small area, it has better thrust efficiency and a long endurance than propeller. Thrust characteristics of hover and for ward flight condition for the ducted fan UAV is important issue to improve a endurance. The unsteady 3-dimensional flow fields of the ducted fan UAV is essential to stable flight. In this paper, to verify the design results of the ducted fan and to investigate a stable aeronautical characteristic, the thrust performance and the unsteady 3-dimensional flow fields are measured. Thrust characteristics for the hovering and the forward flight conditions are measured by the 6-components balance system in the subsonic wind tunnel. The unsteady 3-dimensional flow fields are analyzed by using a stationary
slanted hot-wire technique. The swirl velocity is almost removed behind the stator blades. Therefore, the thrust performance of the ducted fan is improved and the flight stability is maintained.
Prediction of Cut Propagation Direction of Wrinkled Thin Membrane
Kim, Young-Ah ; Woo, Kyeong-Sik ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 5, 2012, Pages 423~430
DOI : 10.5139/JKSAS.2012.40.5.423
In this paper, the effect of wrinkling on the cut propagation direction of thin membrane was studied using geometrically nonlinear shell element post-buckling analysis. In the analysis, rectangular tensile membrane configuration with a slanted center cut was considered. The cut propagation direction was predicted by maximum energy release rate method,
-zero method, and maximum tangential stress method. The cut propagation angle and the
-integral values were calculated for the wrinkled and unwrinkled cases and the results were compared. Various initial cut orientation angles were considered and the effect on the propagation direction was studied. The cut propagation paths were also predicted by virtual cut extension approach.
Non-linear Control of Turbojet Engine for High Maneuverability UAV
Han, Dong-Ju ; Oh, Seong-Hwan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 5, 2012, Pages 431~438
DOI : 10.5139/JKSAS.2012.40.5.431
Non-linear turbojet engine controller with high operational performance has been designed for the high maneuverability UAV. The turbojet engine dynamic performance code has been developed to reflect the non-linear characteristics on controller design, by which the necessity of non-linear controller design was justified by investigating the limitation of linear model derived from the dynamic performance. The PI-like fuzzy controller was designed and enhanced by combining with conventional derivative control. This designed fuzzy controller proves its effectiveness by showing superior control performances over the conventional PID controller along with guaranteeing the safe operation within compressor surge, flame out and turbine temperature limits etc.
COMS Shock Test Assessment by Using the Extrapolation Method
Lee, Ho-Hyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 5, 2012, Pages 439~445
DOI : 10.5139/JKSAS.2012.40.5.439
The COMS(Communication, Ocean, and Meteorological Satellite) is subjected to shock loads when the stage or fairing of a launch vehicle is separated and the satellite is separated from the launch vehicle during the launch vehicle flight. And, after the satellite is separated from the launcher, the COMS is subjected to shock loads when the solar array is deployed, Ka-Band communication antenna is deployed, and meteorological imager radiator cover is released. In order to validate the satellite safety against these shock loads on ground, shock tests were performed. In this paper, the shock tests performed in the course of the COMS development are described, and the method to assess the test result is presented with an example of Geostationary Ocean Color Imager(GOCI). In Ariane-5 launch vehicle, the clampband release shock for satellite separation is lower than the fairing or stage separation. In this paper, the extrapolation method to take into account the maximum shock load from the launch vehicle by using the satellite separation shock test result is also introduced.
Development of System Integration Laboratory for the Verification of UAV Avionics System Requirements
Jo, Young-Wo ; Kim, Bong-Gyu ; Park, Jae-Sung ; Lee, Jae-Uk ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 5, 2012, Pages 446~453
DOI : 10.5139/JKSAS.2012.40.5.446
As part of the integration phases in developing a UAV, a System Integration Laboratory (SIL) has been developed to provide integrated test capability for the verification of avionics system requirements. The SIL has realized primary functions that are common in manned aircraft SIL`s, and specialized laying stress on test data visualization and test automation under the closed-loop structure of the ground control simulation, aircraft simulation and flight simulation components. Those design results have led to easy and sure verification of lots of complex requirements of the UAV avionics system. The functions and performances of the SIL have been proved in four gradational test steps and checked to operate successfully in aircraft System Integration Test Environment for the integration of UAV ground station and aircraft.
Design and implementation of Data Terminal Controller for UAV Using FPGA
Oh, Kyoung-Hwan ; Shim, Hyung-Sik ; Park, Dae-Hwan ; Ra, Sung-Woong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 5, 2012, Pages 454~460
DOI : 10.5139/JKSAS.2012.40.5.454
DTC(Data Terminal Controller) for UAV has been developed using FPGA. It provides the functions of Error Correction and Time-division Mux/Demux for stable data-link. RTOS VxWorks also has been used for real-time control of data-link. FPGA Design of DTC facilitates the modification and extension of various I/O device, and VxWorks ensures real-time availability of data-link control and provides flexibilities of changes of S/W design. The DTC is expected to be deployed easily for various UAV systems.
Design, Implementation and Test of Flight Model of X-Band Transmitter for STSAT-3
Seo, Gyu-Jae ; Lee, Jung-Soo ; Oh, Chi-Wook ; Oh, Seung-Han ; Chae, Jang-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 5, 2012, Pages 461~466
DOI : 10.5139/JKSAS.2012.40.5.461
This paper describes the development and test result of X-band Transmitter flight model(FM) of STSAT-3 by satellite research center(SaTReC), KAIST. The communication sub-system of STSAT-3 is consist of two different frequency band channels. S-band frequency is used for Telemetry & Command, and X-band frequency is used for mission data. Payload observations data in Mass Memory Unit (MMU) is modulated by QPSK modulator in X-band Transmitter, and then QPSK modulation signal is transmitted to antenna through transfer switch. In this Paper, we described the results of modulation, low-pass filter design, power amp development, and switch test. The FM XTU is delivered Spacecraft Assembly, Integration and Test(AIT) level through the completion of functional Test and environmental(vibration, thermal vacuum) Test successfully.