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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 37, Issue 12 - Dec 2009
Volume 37, Issue 11 - Nov 2009
Volume 37, Issue 10 - Oct 2009
Volume 37, Issue 9 - Sep 2009
Volume 37, Issue 8 - Aug 2009
Volume 37, Issue 7 - Jul 2009
Volume 37, Issue 6 - Jun 2009
Volume 37, Issue 5 - May 2009
Volume 37, Issue 4 - Apr 2009
Volume 37, Issue 3 - Mar 2009
Volume 37, Issue 2 - Feb 2009
Volume 37, Issue 1 - Jan 2009
Selecting the target year
Measurement of the Laminar Boundary Layer in a Streamwise Corner by using PIV Technique
Park, Dong-Hun ; Park, Seung-O ; Kwon, Ki-Jung ; Shim, Ho-Joon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 12, 2009, Pages 1165~1172
DOI : 10.5139/JKSAS.2009.37.12.1165
The laminar boundary layer along a streamwise corner formed by two flat plates intersecting at right angle is measured by using Particle Image Velocimetry(PIV) technique. The free stream velocity ranges from 2.96m/s to 3.0m/s. The angle of incidence of the corner is set to 1.2 degree providing slightly favourable pressure gradient to ensure a laminar flow in the corner region. A round shape leading edge is used and the length of the model is about 1000mm. In the bisector plane, the measurement data show separation type velocity profiles having an inflection point which is a typical characteristic of laminar corner boundary layers. As the distance away from the bisector plane increases, velocity profiles are found to change into the Blasius profile. The change completes around half length of the boundary layer thickness in the bisector plane away from the bisector plane along the plate. In the bisector plane, the growth characteristic of the boundary layer thickness and the approximate similarity of velocity profiles are confirmed from the measurement data.
Flow Control of Smart UAV Airfoil Using Synthetic Jet Part 1 : Flow control in Hovering Mode Using Synthetic Jet
Kim, Min-Hee ; Kim, Sang-Hoon ; Kim, Woo-Re ; Kim, Chong-Am ; Kim, Yu-Shin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 12, 2009, Pages 1173~1183
DOI : 10.5139/JKSAS.2009.37.12.1173
In order to reduce the download around the Smart UAV(SUAV) at hovering, flow control using synthetic jet has been performed. Many of the complex tilt rotor flow features are captured including the leading and trailing edge separation, and the large region of separated flow beneath the wing. In order to control the leading edge and trailing edge separation, synthetic jet is located at 0.01c,
. As non-dimensional frequency, the flow pattern is altered and the rate of drag reduction is changed. The results show that synthetic jets shorten the vortex period and decrease the vortex size by changing local flow structure. By using leading edge jet and trailing edge jet, download is efficiently reduced compared to no control case at hovering mode.
Flow Control of Smart UAV Airfoil Using Synthetic Jet Part 2 : Flow control in Transition Mode Using Synthetic Jet
Kim, Min-Hee ; Kim, Sang-Hoon ; Kim, Woo-Re ; Kim, Chong-Am ; Kim, Yu-Shin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 12, 2009, Pages 1184~1191
DOI : 10.5139/JKSAS.2009.37.12.1184
In order to reduce the download around the Smart UAV(SUAV) at Transition mode, flow control using synthetic jet has been performed. Many of the complex tilt rotor flow features are captured including the leading and trailing edge separation, and the large region of separated flow beneath the wing. Based on the results of part 1 of the present work, synthetic jet is located at 0.01c,
and it is operated with the non-dimensional frequency of 0.5, 5 to control the leading edge and trailing edge separation. Consequently, download is substantially reduced compared to with no control case at transition mode using leading edge jet only. The present results show that the overall flight performance and stability of the SUAV can be remarkably improved by applying the active flow control strategy based on synthetic jet.
A Study on the Aileron Reversal Characteristics of CAS Composite Aircraft Wings
Song, Oh-Seop ; Kim, Keun-Taek ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 12, 2009, Pages 1192~1200
DOI : 10.5139/JKSAS.2009.37.12.1192
This paper deals with an analytical study on the aileron reversal characteristics of anisotropic composite aircraft wings modelled as thin-walled beam and having bending-torsion structural couplings caused by Circumferentially Asymmetric Stiffness layup scheme. For a study on the aileron reversal of CAS composite wings, it is essential to consider the following effects such as warping restraint, transverse shear flexibility, bending-twist structural coupling, wing aspect ratio, ratio of span-wise and chord-wise length of aileron to wing, and sweep angle, etc. The results on the aileron reversal could have a significant role in more efficient designs of thin-walled composite wing aircraft for which this aeroelastic instability is one of the most critical ones.
Evaluation of Formability of Copper Alloy for Regenerative Cooling Chamber before and after Heat Treatment
Ryu, Chul-Sung ; Lee, Keum-Oh ; Choi, Hwan-Seok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 12, 2009, Pages 1201~1208
DOI : 10.5139/JKSAS.2009.37.12.1201
Dome stretching tests and tension tests were performed to evaluate the formability of a copper alloy used for manufacturing the regenerative cooling chamber. The test specimens were prepared to investigate the effect of heat treatment and direction of specimens on the formability. The test results show that forming limit values are increased by the heat treatment of the material but the variation of the forming limit values by manufacturing direction is negligible compared to the heat treatment effect, and forming limit values are also different according to the test methods. These results indicate that the high temperature heat treatment of the material before bulging is a very important process to deform the inner cylindrical structure of the regenerative cooling chamber into a nozzle shape by the bulging process without necking or fracture and the test methods also have a great effect on a evaluation of the formability. The forming limit diagram obtained in this study would be utilized to the design of regenerative cooling chamber nozzles.
Vision-based Small UAV Indoor Flight Test Environment Using Multi-Camera
Won, Dae-Yeon ; Oh, Hyon-Dong ; Huh, Sung-Sik ; Park, Bong-Gyun ; Ahn, Jong-Sun ; Shim, Hyun-Chul ; Tahk, Min-Jea ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 12, 2009, Pages 1209~1216
DOI : 10.5139/JKSAS.2009.37.12.1209
This paper presents the pose estimation of a small UAV utilizing visual information from low cost cameras installed indoor. To overcome the limitation of the outside flight experiment, the indoor flight test environment based on multi-camera systems is proposed. Computer vision algorithms for the proposed system include camera calibration, color marker detection, and pose estimation. The well-known extended Kalman filter is used to obtain an accurate position and pose estimation for the small UAV. This paper finishes with several experiment results illustrating the performance and properties of the proposed vision-based indoor flight test environment.
Autonomous Aerobatic Flight for Fixed Wing Aircraft
Park, Sang-Hyuk ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 12, 2009, Pages 1217~1224
DOI : 10.5139/JKSAS.2009.37.12.1217
A simple and effective guidance and control scheme that enables autonomous three-dimensional path-following for a fixed wing aircraft is presented. The method utilizes the nonlinear path-following guidance law for the outer loop that creates steering acceleration command based on the desired flight path and the current position and velocity of the vehicle. The scheme considers the gravity in the guidance level, where it is subtracted from the acceleration command to form the specific force acceleration command which the aircraft is better suited to follow than the total acceleration command in the inner-loop. A roll attitude control scheme is also presented that enables inverted flight or sideslip maneuvers such as slow roll and knife-edge. A series of aerobatic maneuvers are demonstrated through simulations to show the potential of the proposed scheme.
Design of Fault Isolator of Satellite Reaction Wheel System Using Dual Filter and Multi-hypothesis Extended Kalman Filter
Choi, Kwang-Rok ; Park, Chan-Gook ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 12, 2009, Pages 1225~1231
DOI : 10.5139/JKSAS.2009.37.12.1225
One reaction wheel cluster of satellite usually has four reaction wheels. Each wheel is not arranged parallel to the attitude axis of satellite. Therefore, if one reaction wheel is broken, it is very hard to isolate the fault except using the sensors of wheel itself. In this paper, the isolator of satellite reaction wheel cluster is designed. Using a dual filter, FDP(Fault Detection Parameter) is made to detect fault, and using a multi-hypothesis extended Kalman filter, fault isolation of wheel cluster is done. We verify the improvement of isolation performance of wheel cluster by simulation with 4-reaction wheel cluster.
Development of B-Value Based GBAS Ground Facility Error Standard Deviation Model and Verification
Jun, Hyang-Sig ; Ahn, Jong-Sun ; Lee, Young-Jae ; Choi, Young-Kiu ; Sung, Sang-Kyung ; Yeom, Chan-Hong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 12, 2009, Pages 1232~1237
DOI : 10.5139/JKSAS.2009.37.12.1232
The ICAO and FAA are developing and verifying of GBAS for civil aircraft landing and take-off. The guarantee of aircraft integrity issue is the important part of GBAS. To guarantee integrity, the GBAS ground facility broadcasts various informations to aircraft. The informations are related to the estimated accuracy of each pseudorange correction and the estimated error terms, for example B-value and standard deviation of the ground facility error. These parameters are used to calculate position error (estimated value of the user). If estimated position errors don't satisfy requirements, aircraft use alternate navigation means. In this paper, GBAS reference stations's real data, which operated by KARI (Korea Aerospace Research Institute) in Jeju international airport, are used to development of new ground facility error standard deviation model. We verify improvement of GBAS availability, with respected to vertical protection level, using B-value based a new ground facility error standard deviation model and a sigma inflation factor.
Study of On-line Performance Diagnostic Program of A Helicopter Turboshaft Engine
Kong, Chang-Duk ; Koo, Young-Ju ; Kho, Seong-Hee ; Ryu, Hyeok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 12, 2009, Pages 1238~1244
DOI : 10.5139/JKSAS.2009.37.12.1238
This work proposes a GUI-type on-line diagnostic program using SIMULINK and Fuzzy-Neuro algorithms for a helicopter turboshaft engine. During development of the diagnostic program, a look-up table type base performance module for reducing computer calculating time and a signal generation module for simulating real time performance data are used. This program is composed of the on-line condition monitoring program to monitor on-line measuring performance condition, the fuzzy inference system to isolate the faults from measuring data and the neural network to quantify the isolated faults. The reliability and capability of the proposed on-line diagnostic program were confirmed through application to the helicopter engine health monitoring.
Thermal Performance Evaluations on High-Erosion Resistance Materials for Very Small Nozzle Throat Inserts
Kang, Yoon-Goo ; Park, Jong-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 12, 2009, Pages 1245~1251
DOI : 10.5139/JKSAS.2009.37.12.1245
This paper describes the research on the non-eroding throat insert materials under condition of high-temperature, high-pressure, and long-burn time. C/SiC, CIT and W/
were chosen and tested in thermal protection evaluation motor of burning time 20 seconds. From the test results, a heat resistance of W/
was the most excellent among them, but was happened crack on material surface. Thermal reaction characteristics and heat resistance of these materials and feasibility of W/
as throat material were ascertained.
Development of an Off-line 6-DOF Simulation Program for Store Separation Analysis
Kwak, Ein-Keun ; Shin, Jae-Hwa ; Lee, Seung-Soo ; Choi, Kee-Young ; Hyun, Jae-Soo ; Kim, Nam-Gyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 12, 2009, Pages 1252~1257
DOI : 10.5139/JKSAS.2009.37.12.1252
Off-line 6-DOF simulation program for store separation analysis has been developed. The developed program enables to predict a trajectory of a store from the database which was constructed by wind tunnel testing or CFD analysis. The flow angle method was applied to the program for predicting aerodynamic coefficients from the database and the ejector forces and constraints were enabled to incorporate the equations of motion for computing the trajectory. Using the program, the trajectories were calculated and the results are compared with the CTS results.
Engineering Qualification Model Design and Implementation of Mass Memory Unit for STSAT-3
Seo, In-Ho ; Oh, Dae-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 12, 2009, Pages 1258~1263
DOI : 10.5139/JKSAS.2009.37.12.1258
This paper describes the design and test results of engineering qualification model(EQM) of mass memory unit(MMU) for STSAT-3. The MMU for STSAT-3 having 32Gb mass memory capacity is capable of receiving and transmitting the mission data from MIRIS(Multi-purpose IR Imaging System) and COMIS(Compact Imaging Spectrometer) at 100Mbps and 10Mbps. The performance of EQM MMU was verified by the tests of data receiving from two payloads and data transmission to the data receiving system. Moreover, the vibration and thermal vacuum test was performed to verify the launch vehicle and space environments.