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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 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
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Aerodynamic Characteristics of the Blended-Wing-Body for the Position and Aspect Ratio of the Inlet and Outlet of an Embedded Distributed Propulsion System
Kim, Hyo-Seop ; Choi, Hyun-Min ; Cho, Jin-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 6, 2012, Pages 467~474
DOI : 10.5139/JKSAS.2012.40.6.467
UAVs for reconnaissance and intelligence operations require long endurance capability, which demands high efficiency of the propulsion system. The distributed propulsion system(DPS) generates the thrust by replacing a large propulsion system with a number of small propulsion systems. A DPS distributed along the wing span can produce gains in propulsion efficiency by reducing ejection velocity. Also, the ingestion of boundary layers through the distributed DPS inlet and ejecting flow from the outlet can improve the lift to drag ratio of the vehicle. This study investigates the effects of locations and size of the inlet and outlet of the DPS on the blended-wing-body design based on Eppler 337 airfoil, with a CFD tool. The fans in the DPS are modeled as actuator disks for computational efficiency. The best location and aspect ratio of the inlet and outlet are found from lift-to-drag ratio and pitching moment considerations.
Numerical Study of the Aerodynamic Characteristics of an Airfoil with Thickness Uncertainty for a Wind Tunnel Testing
Yi, Tae-Hyeong ; Kwon, Ki-Jung ; Kim, Keun-Taek ; Ahn, Seok-Min ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 6, 2012, Pages 475~484
DOI : 10.5139/JKSAS.2012.40.6.475
Numerical investigation is performed to understand the effects of thickness uncertainty of a supporting airfoil due to manufacturing processes on the aerodynamic characteristics of an airfoil used for measuring data in a wind tunnel testing. This is done by comparing the coefficients of lift, drag and moment of the airfoils. In this work, the airfoil model consists of three parts, one located in the center for measuring and two outer parts used for supporting. The study is carried out with a NACA64-418 airfoil and the turbulence model of Transition SST. It is found that the effect of thickness uncertainty of the airfoils used for supporting is not significant to the performance of the test airfoil at various angles of attack and Reynolds numbers.
A Study on Wall Interference Effect Around the Wind Turbine Airfoil
Cho, Hwan-Kee ; Kang, Seung-Hee ; Ryu, Ki-Wahn ; Lee, Jun-Shin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 6, 2012, Pages 485~491
DOI : 10.5139/JKSAS.2012.40.6.485
The wall interference effects around the wind-turbine airfoil are experimentally investigated at low Reynolds numbers in a closed test-section wind tunnel. The test is performed at free-stream velocities from 10 to 31 m/s, which correspond to Reynolds numbers ranging from
based on chord of the airfoil. The blockage-area ratios, which is the ratio of the chord to the test-section width, are 27.8%, 38.5%, 41.7%, 45.5%, and 55.6%. The test results for the airfoil show that the transition point on the airfoil surface tends to move backward due to wall interference. The wall pressures for an adequate interference correction by a measured-boundary-condition method are desirable more than three times region of the chord before and after around the reference center.
Study on Characteristics of DBD Plasma Actuator as Design Parameters for Plasma Flow Control
Yun, Su-Hwan ; Kwon, Hyeok-Bin ; Kim, Tae-Gyu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 6, 2012, Pages 492~498
DOI : 10.5139/JKSAS.2012.40.6.492
Characteristics of DBD(Dielectric Barrier Discharge) plasma actuator as design parameters were investigated for plasma flow control. Flow velocity and power consumption of the DBD plasma actuator were measured according to the design parameters such as discharge voltage and frequency, gap, width and length of electrode, and the thickness of dielectric barrier. The flow velocity and power consumption increased as the discharge voltage and frequency increased. As the electrode gap increased, the flow velocity increased with decreasing the power consumption, whereas high voltage was required for the plasma discharge. The flow velocity increased as the upper-electrode width decreased, and as the lower-electrode width increased at the constant power consumption. The performance of the DBD plasma actuator can be estimated at the given discharge and geometry conditions.
Structural Design and Analysis upon Active Rotor Blade with Trailing-edge Flap
Eun, Won-Jong ; Natarajan, Balakumaran ; Lee, Jae-Hwan ; Shin, Sang-Joon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 6, 2012, Pages 499~505
DOI : 10.5139/JKSAS.2012.40.6.499
Vibratory loads imposed by the rotating blade upon the fuselage has been one of major obstacles in rotorcrafts. A new concept of rotor blade is currently developed to adopt an Active Trailing-edge Flap (ATF) to alleviate such obstacles. The flap is mounted at 65~85% spanwise location from the rotor hub. The nominal rotational speed of the blade is as high as 1,528 RPM, to match the required tip Mach number. Structural integrity is one of the important design aspects to be maintained and monitored in this special type of rotor. This is due to that many detailed components, which drive the flap, are inserted inside the rotating blade. To conduct its structural design and analysis, CAMRAD-II and the one-dimensional beam analysis are used. At the same time, three-dimensional finite element analysis are also used, such as MSC. PATRAN/NASTRAN, in order to analyze the details of the present active blade. As a result, comparable characteristics for the present rotor are predicted by both approaches.
Design a Path Following Line-of-Sight Guidance Law based on Vehicle Kinematics
You, Dong-Il ; Shim, Hyun-Chul ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 6, 2012, Pages 506~514
DOI : 10.5139/JKSAS.2012.40.6.506
This paper represents a method for designing of path following Line-of-Sight(LOS) guidance law based on vehicle kinematics. In general, a LOS guidance law which is composed of gains and approach length as design parameters is designed by empirical or trial-and-error method. These approaches cannot guarantee a precision tracking performance of guidance law consistently. Also, the design parameters should be redesigned with variations of vehicle maneuverability and flight velocity. Based on a vehicle kinematics with its velocity, the proposed method for designing of parameters not only minimizes the number of design parameters, also has a reliable and consistent tracking performance using variable guidance gain changed in accordance with flight velocity. This is validated by nonlinear simulation with
order attitude response dynamics and flight experiments with given linear and circular path.
A Study on Algorithm for Aircraft Collision Avoidance Warning
Jung, Myung-Jin ; Jang, Se-Ah ; Choi, Kee-Young ; Kim, Jin-Bok ; Yang, Kyung-Sik ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 6, 2012, Pages 515~522
DOI : 10.5139/JKSAS.2012.40.6.515
CFIT(Controlled Flight Into Terrain) is one of the major causes of aircraft accidents. In order to solve this problem, GPWS(Ground Proximity Warning System) is used to generate terrain collision warning using the distance between the aircraft and the underneath ground. Since the GPWS uses the vertical clearance only, it frequently generates false warnings. In this study, a terrain/obstacle collision avoidance warning algorithm was developed for fast flying and highly maneuvering fighters using the flight status and the geographic information. This algorithm condsiders the overall delay in the aircraft reactive motion including the pilot's reaction time. The paper presents a detailed logic and test methods.
Energy Balance and Constraints for the Initial Sizing of a Solar Powered Aircraft
Hwang, Ho-Yon ; Nam, Tae-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 6, 2012, Pages 523~535
DOI : 10.5139/JKSAS.2012.40.6.523
Solar powered aircraft are becoming more and more interesting for future long endurance missions at hight altitudes, because they could provide surveillance, earth monitoring, telecommunications, etc. without any atmospheric pollution and hopefully in the near future with competitive costs compared with satellites. However, traditional aircraft sizing methods currently employed in the conceptual design phase are not immediately applicable to solar powered aircraft. Hence, energy balance and constraint analyses were performed to determine how various power system components effect the sizing of a solar powered long endurance aircraft. The primary power system components considered in this study were photovoltaic (PV) modules for power generation and regenerative fuel cells for energy storage. To verify current research results, these new sizing methods were applied to HALE aircraft and results were presented.
Design of Instrumented Pod for Flight Aeroacoustic Environment
Jun, Oo-Chul ; Kim, Sang-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 6, 2012, Pages 536~541
DOI : 10.5139/JKSAS.2012.40.6.536
An instrumented pod has been developed to measure the aeroacoustic environment as well as the conventional data such as load, vibration, and aerodynamic heating of fighters during flight tests, confirming to the recently developed external pod design for fighters. This study presents the development of the measurement system in detail, being the first indigenous effort in its kind. The pod was designed to meet the requirements of the MIL-HDBK-1763 and MIL-STD-810 Method 515, which are the base to determine the locations and range of sensors. The Endevco 8510B-2 was selected as the sensor to withstand the harsh environment during the flight tests. In order to assess the integrity of the fabricated pod design, a ground run-up test of a KF-16 has been conducted with the pod installed at Station 5. The test results show that the system works well but the sound level exceeds the predetermined sensor range. The sensor range has been readjusted for flight test performed later.
Development of Ground Control Software for Operation of Multiple Unmanned Aerial Vehicles
Shin, Yoon-Ho ; Cho, Sang-Wook ; Jo, Sung-Beom ; Kim, Sung-Hwan ; Lyu, Chang-Kyung ; Choi, Kee-Young ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 6, 2012, Pages 542~547
DOI : 10.5139/JKSAS.2012.40.6.542
Until recently, most of GCS(Ground Control Software) has been required to visualize attitude, position, status of vehicle and to transmit control and mission commands for a single UAV(Unmanned Aerial Vehicle). However, the GCS needs to expand its functions to handle more complex situations. Simultaneous operation of multiple UAVs is emerging as a new practice. Hence, we set up requirements for operation of multiple UAVs and suggest the architecture of GCS that satisfy the requirements. In this study, we analyze the upper requirements and define the total structure of GCS at first. Then we design the inner structure for requirements in detail. Finally, we verify the functions of GCS on PILS(Processor In the Loop Simulation) System.
Development of Verification Environment for Flight Safety Critical Software using NEXUS
Yoon, Hyung-Sik ; Han, Jong-Pyo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 6, 2012, Pages 548~554
DOI : 10.5139/JKSAS.2012.40.6.548
Verification and validation of operational software of the flight control computer, which is flight safety critical, is very important to prove correctness and faultness of the software. To verify the real-time softare requirement on operational software of flight control computer, real-time software internal parameter and variable monitoring technics on hardware-in-the-loop environment, similar to on-flight environment, is required. This paper describes flight safety critical software validation and verificiation environment using standard debugging interface, NEXUS 5001.