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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
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Journal DOI :
The Korean Society for Aeronautical & Space Sciences
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Volume & Issues
Volume 44, Issue 9 - Sep 2016
Volume 44, Issue 8 - Aug 2016
Volume 44, Issue 7 - Jul 2016
Volume 44, Issue 6 - Jun 2016
Volume 44, Issue 5 - May 2016
Volume 44, Issue 4 - Apr 2016
Volume 44, Issue 3 - Mar 2016
Volume 44, Issue 2 - Feb 2016
Volume 44, Issue 1 - Jan 2016
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Free-fall Force Measurement in a Shock Tunnel
Park, Jinwoo ; Chang, Won Keun ; Park, Gisu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 6, 2016, Pages 463~467
DOI : 10.5139/JKSAS.2016.44.6.463
In this paper, acceleration and pressure exerted on a human model were measured under a supersonic condition in a shock tunnel. In order to measure these in an interference-free environment, free-fall technique with an electromagnet and a three-dimensional iron-powdered human model was used. Free-fall experiment was conducted at Mach 4 and the force acting on the model was obtained by calculating the displacement from the flow visualization images.
Optimal Design for a Conic Winglet of a Dual Type Combined Fan
Kim, Jin-Wook ; Kim, Woo-Teak ; Ryu, Min-Hyoung ; Cho, Lee-Sang ; Cho, Jin-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 6, 2016, Pages 468~476
DOI : 10.5139/JKSAS.2016.44.6.468
In this study, the conic winglet which is made by rotating wing tip airfoil by each 3 axis is applied to the dual type combined fan to reduce the wing tip leakage loss. Computational Fluid Dynamics is used to calculate the loss and optimum technique is used to get minimum loss. Optimization results shows that total pressure loss coefficient was reduced by 3.4 %, and optimization model was a bended shape at the end of wing forward to pressure side.
Velocity profile measurement of supersonic boundary layer over a flat plate using the PIV technique
Lee, Hyuk ; Kim, Young Ju ; Byun, Yung Hwan ; Park, Soo Hyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 6, 2016, Pages 477~483
DOI : 10.5139/JKSAS.2016.44.6.477
Velocity profiles of laminar, transition and turbulent boundary layers were investigated by using Particle Image Velocimetry(PIV) measurements on the flat plate at Mach 2.96. The Schlieren visualization and PIV measurements are also used to confirm whether the oblique shock wave generated from the leading edge affects the flow field over the flat plate. The laminar velocity profile measured from the experiment was well matched with the compressible Blasius solution. The velocity profile of the transition boundary layer was well correlated with the theoretical turbulent velocity profile from near the wall and the transition began from Re
Development of composite torsion shaft for the aircraft structure under multiple load condition
Jeong, Jong-Jae ; Kim, Seung-Chul ; Kim, Jeong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 6, 2016, Pages 484~491
DOI : 10.5139/JKSAS.2016.44.6.484
The purpose of this development is weight reduction of hollow type steel torque bar by changing the material from steel to composite. Structure analysis is executed by the finite element model generated by the structural load condition and geometric structure requirement. According to this analysis result, optimized ply sequence and wall thickness are defined. To simulate analysis result, torsion test for composite torque bar was performed. Throughout the test result, the stiffness and strength requirement of composite torque bar was verified.
Stability Analysis of Three-Loop Autopilot with respect to IMU Position and C.G Variation Rate in Guided Missiles
Kwon, Hyuck-Hoon ; Kim, Yoon-Hwan ; Park, Bong-Gyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 6, 2016, Pages 492~501
DOI : 10.5139/JKSAS.2016.44.6.492
Three-Loop autopilot is generally used for the acceleration control of guided missiles. Because the acceleration command to the three-loop autopilot is given as values at the center of gravity, feedback information of IMU should be obtained at the same position. However, the position of IMU might not be located at the center of gravity due to the sub-system assignment. This paper presents the stability analysis of three-loop autopilot with respect to the arbitrary position of IMU and variation rate of center of gravity. Gain and phase margins are calculated for several trim points for general anti-tank missiles.
A Precise Projectile Trajectory Registration Algorithm Based on Weighted PDOP
Shin, Seok-Hyun ; Kim, Jong-Ju ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 6, 2016, Pages 502~511
DOI : 10.5139/JKSAS.2016.44.6.502
Recently, many kind of smart projectiles are being developed. In case of smart projectile, studying in advance, it uses a navigation data acquired from the GNSS receiver to check its location on the geocentric(WGS84) coordinates and to estimate P.O.I(point of impact). However, because of various error inducing factors, the result of positioning involve some errors. We introduce the advanced algorithm for the reconstruction of a navigation trajectory using weighted PDOP, based on a simulated trajectory acquired from PRODAS. It is very fast and robust to noise and shows reliable output. It can be widely used to estimate an actual trajectory of a projectile.
Studies on the improvement of driving gears quality at Inlet Guide Vane of aircraft auxiliary power unit
Park, Sungjae ; Park, Sunwook ; Suh, Jaekyoung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 6, 2016, Pages 512~519
DOI : 10.5139/JKSAS.2016.44.6.512
Auxiliary Power Unit of FA-50 which provides energy other than propulsion is an important element to maintain airworthiness on aircraft. Also Inlet Guide Vane of Auxiliary Power Unit is a device that supplies appropriate airflow into the Auxiliary Power Unit after adjusting influent airflow into the load compressor. This report, based on the problems occurred the driving gears of Inlet Guide Vane, deals with cause of occurrence, troubleshooting, design improvement and result of test flight verification for FA-50 aircraft Auxiliary Power Unit lifespan.
Reverse-Engineering and Analysis of Performance for Medium-Altitude Long Endurance Unmanned Aerial Vehicle
Shim, Ho-Joon ; Chang, Kyoungsik ; Chung, In Jae ; Kim, Sun-Tae ; Joh, Chang-Yeol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 6, 2016, Pages 520~529
DOI : 10.5139/JKSAS.2016.44.6.520
The main purpose of this study was to analyze the performance of a medium-altitude long endurance unmanned aerial vehicle through reverse-engineering method. The external configuration data of the RQ-1 Predator was reverse-engineered from related photos and specification data available on public domains, which also were used to generate the CATIA modeling and weigh distribution data of the UAV. The aerodynamic characteristics of RQ-1 Predator were mainly predicted the vortex lattice method and an empirical method, which the propeller performance was analyzed by the empirical method proposed by Howe. The rate of climb, service ceiling, range, and the loiter endurance of the UAV was analyzed, which showed good agreement with the reference data.
A Design of Handling Quality Assessment Environment Based on FLIGHTLAB Model Using Legacy Simulator
Yang, Chang Deok ; Lee, Seung Deok ; Cho, Hwan Heui ; Jung, Dong Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 6, 2016, Pages 530~536
DOI : 10.5139/JKSAS.2016.44.6.530
The handling quality simulator including high fidelity flight mechanics model is indispensable component to design and verify the flight control system. Korea Aerospace Industries, LTD. (KAI) has been performing LCH (Light Civil Helicopter) core technology development program regarding automatic flight control system (AFCS) software development. And KAI has been developing flight mechanics model using FLIGHTLAB to design and evaluate the AFCS flight control law. This paper presents the handling quality assessment environment development results through the combining FLIGHTLAB with a legacy simulator. And this paper details the FLIGHTLAB model, application development process and FLIGHTLAB interface design. The developed handling quality assessment environment has been demonstrated with the ADS-33E hover and pirouette MTE (Mission Task Element) maneuver simulation.
Pitching Moment Coefficient Modeling of KF-16 using Adaptive Design of Experiments with cost consideration
Lee, Don-Goo ; Jin, Hyeon ; Ahn, Jaemyung ; Lee, Yeongbin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 6, 2016, Pages 537~543
DOI : 10.5139/JKSAS.2016.44.6.537
A new approach to systematically model aerodynamic coefficients using an adaptive sampling based wind tunnel testing considering cost is proposed. The Latin Hypercube design is used for selecting initial test points. The Gaussian Process (GP) is iteratively used during the experiment to determine additional experimental points that minimizes the uncertainty reduction per incremental cost. A numerical simulation based experiment was conducted using the static aerodynamic coefficient database a fighter aircraft, which demonstrated the validity of the proposed method.