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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
Selecting the target year
Eulerian-based Numerical Modeling for Impingement Prediction of Supercooled Large Droplets
Jung, Sung-Ki ; Kim, Ji-Hong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 8, 2012, Pages 647~654
DOI : 10.5139/JKSAS.2012.40.8.647
Supercooled large droplet issues in aircraft icing have been continually reported due to the important safety considerations. In order to simulate the impingement behavior of large droplets, a two-dimensional and compressible Navier-Stokes code was developed to determine the flow field around the test model. Also, the Eulerian-based droplet impingement model including a semi-empirical approach for the droplet-wall interaction process and droplet break-up was developed. In particular, the droplet-wall interactions were considered as numerical boundary conditions for the droplet impingement simulation in the supercooled large droplet conditions. Finally, the present results were compared with the experimental test data and the LEWICE results. The droplet impingement area and maximum collection efficiency values between present results and wind tunnel data were in good agreements. Otherwise, the inclination of collection efficiency of the present result is over-predicted than the wind tunnel data around a lower surface of the NACA 23012 airfoil.
Aerodynamic Drag Prediction of a Bearingless Rotor Hub
Kang, Hee-Jung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 8, 2012, Pages 655~661
DOI : 10.5139/JKSAS.2012.40.8.655
In this study, aerodynamic drag of a bearingless rotor hub was predicted by computational fluid dynamics methodology using unstructured overset mixed meshes. The calculated results showed that the drag due to pressure forces rather than the viscous drag act as a major factor on both the fuselage and rotor hub, and the drag acting on the torque tube accounted for the largest portion in the hub drag. It was also found the hub drag accounted for 39 ~ 41% of the fuselage drag. Finally, the result confirmed the drag of the designed rotor hub satisfied the requirement of the aerodynamic hub drag by comparing with the drag trend of developed helicopter.
The Effect of Aspect Ratio on the Aerodynamic Characteristics of an Insect-based Flapping Wing
Han, Jong-Seob ; Chang, Jo-Won ; Jeon, Chang-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 8, 2012, Pages 662~669
DOI : 10.5139/JKSAS.2012.40.8.662
The effect of aspect ratio (AR) on the aerodynamic characteristics of a flapping wing was examined to analyze the design parameters of an insect-based MAV. The experimental model constructed with 4-bar linkages was operated in a water tank with the condition of a low Reynolds number. A water-proof micro-force load cell was fabricated and installed at the root of the wing which is made of a plexiglas. The wing shapes were based on the planform of a fruit fly wing. The ARs selected were 1.87, 3.74 and 7.48 and the Reynolds number was fixed at
. For AR
Prediction of Mechanical Property of Biomorphic Composites
Jeong, Jae-Yeon ; Woo, Kyeong-Sik ; Lee, Dong-Ju ; Hong, Soon-Hyung ; Kim, Yun-Chul ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 8, 2012, Pages 670~677
DOI : 10.5139/JKSAS.2012.40.8.670
In this paper, mechanical property of biomorphic C/SiC composite was calculated by unit cell analysis. The microstructural arrangements of carbonized pine and radiata pine which were impregnated with silicon, were idealized as square and hexagonal arrays. Unit cell was then defined and equivalent elastic constants were calculated. A single and double unit cell structures were considered. The effect of void distribution was also studied by monte carlo simulation.
Design and Validation of Model Inversion Flight Control Law for Fly By Wire Helicopter
Kim, Chong-Sup ; Cho, In-Je ; Lee, Seung-Duck ; Lee, Han-Ju ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 8, 2012, Pages 678~687
DOI : 10.5139/JKSAS.2012.40.8.678
The Fly-By-Wire(FBW) flight control system is essential to improve the stability and flying quality of the helicopter. Advanced aerospace companies, such as Bell-Sikorsky (USA) and NHI (European Consortium), have already applied the FBW flight control system to manufacture V-22 and NH-90 helicopters, respectively. This paper addresses the development of control law design using model inversion method improve the hover and low speed handling qualities of helicopter based on BO-105 model in `Day` and `Degraded visual environments(DVEs)` in accordance with ADS-33E-PRF. Design parameters are optimized to satisfy the handling qualities specification using Control Designer`s Unified Interface (CONDUIT) commercial control law software. The result of the analysis based on CONDUIT and non-real time simulation in-house software, HETLAS (HElicopter Trim Linearization And Simulation) reveals that the provides an efficient mean to achieve Level 1 handling qualities.
A Study on the Effect of Engine Nozzle Configuration on the Plume IR Signature
An, Sung-Yong ; Kim, Won-Cheol ; Oh, Seong-Hwan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 8, 2012, Pages 688~694
DOI : 10.5139/JKSAS.2012.40.8.688
A study on the effect of engine nozzle configuration on the engine plume Infra-red (IR) signature characteristics is performed. Configuration design of an engine nozzle with high aspect ratio to reduce IR signature level and a cylindrical nozzle which is typically used for conventional aircraft which does not require IR signature reduction is performed. And CFD analysis for the two nozzles is performed to compare the flowfields characteristics of the two nozzles. Finally IR signature analysis for the two nozzles is accomplished to calculate the total intensity level at mid-wave infra-red and investigate the differences of IR signature characteristics between the two nozzles.
Multidisciplinary UAV Design Optimization Implementing Multi-Fidelity Analysis Techniques
Lee, Jae-Woo ; Choi, Seok-Min ; Van, Nguyen Nhu ; Kim, Ji-Min ; Byun, Yung-Hwan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 8, 2012, Pages 695~702
DOI : 10.5139/JKSAS.2012.40.8.695
In this study, Multi-fidelity analysis is performed to improve the accuracy of analysis result during conceptual design stage. Multidisciplinary Design Optimization(MDO) method is also considered to satisfy the total system requirements. Low-fidelity analysis codes which are based on empirical equations are developed and validated for analyzing the Unmanned Aerial Vehicle(UAV) which have unconventional configurations. Analysis codes consist of initial sizing, aerodynamics, propulsion, mission, weight, performance, and stability modules. Design synthesis program which is composed of those modules is developed. To improve the accuracy of the design method for UAV, Vortex Lattice Method is used for the strategy of MFA. Multi-Disciplinary Feasible(MDF) method is used for MDO technique. To demonstrate the validity of presented method, the optimization results of both methods are compared. According to those results, the presented method is demonstrated to be applicable to improve the accuracy of the analyses during conceptual design stage.
Systematic Determination of Empirical Parameters Used in Helicopter Conceptual Design
Kim, Won-Jin ; Chae, Sang-Hyun ; Oh, Se-Jong ; Kim, Seung-Bum ; Ahn, Iee-Ki ; Yee, Kwan-Jung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 8, 2012, Pages 703~710
DOI : 10.5139/JKSAS.2012.40.8.703
At the stage of conceptual design of a helicopter, it is a general way using low fidelity analysis methods because of a large number of design calculations and trade-off studies. Determination of empirical parameters used in analysis codes for more practical design, depends on an user`s design experiences, which effects on the accuracy and the fidelity of conceptual design results. Thus, more precise and logical method should be required to determine the empirical parameters used in the conceptual design of a helicopter. The present method is to be used not only in verifying the empirical parameters generated by design requirements, but also regenerate them if they contain any errors. Empirical parameters produced by present method were used to design a helicopter with a payload objective and performance constraints of an operating helicopter. As a result, weights and geometries of designed helicopter matched the target value within 5% significance level, proving that the suggested parameter generating method can be useful in the conceptual design of a helicopter.
A Wind Tunnel Study on the Static Stability Characteristics of Light Sport Aircraft
Kim, Jong-Bum ; Jang, Young-Il ; Kwon, Ky-Beom ; Chung, Hyoung-Seog ; Cho, Hwan-Kee ; Kim, Sang-Ho ; Lee, Jae-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 8, 2012, Pages 711~717
DOI : 10.5139/JKSAS.2012.40.8.711
During the conceptual design phase of a light sport aircraft, the wind tunnel tests were conducted to investigate the static stability of newly-designed configuration. The 1/5 scale-down wind tunnel model consisted of fuselage, main wing, vertical tail and horizontal tail. The main wing and tails were able to be attached or detached from the fuselage. The aerodynamic forces and moments acting on the 6 different configurations compounding each component were measured by using the internal balance system and their static stability derivatives were derived. With these experimental data, the baseline lift and drag characteristics as well as the effects of each component to the longitudinal, directional and lateral static stability were quantitatively analyzed.
A Study on the Performance Prediction of Fire Extinguish System in Aircraft Engine Bay
Park, Young-Ha ; Kim, Hyung-Sik ; Kim, Jin-Han ; Cho, Soo-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 8, 2012, Pages 718~725
DOI : 10.5139/JKSAS.2012.40.8.718
Fuel or oil which is leaked into the aircraft engine bay can make a fire when it is contacted to the engine surface of hot temperature. In order to avoid fire, the fire extinguish system should be designed so that the extinguishing agent is quickly injected and its concentration keeps higher in the fire protection region. FAA requires that the extinguishing agent injected within the fire protection region should be sustained longer than 0.5 second on keeping a higher concentration than 6%. For developing a fire protection system satisfying the FAA regulation, numerical and experimental studies for the injection time and the concentration of the extinguishing agent were conducted. These results showed similar trend for the injection time or concentration, but the data acquisition was delayed due to the response of the sensors in the experiment.
Design for Spin/Stall Recovery Parachute System of Turbo-prop Airplane
Lee, Dong-Hun ; Nho, Byung-Chan ; Kang, Myung-Kag ; Kang, Gyeong-Woo ; Lee, Ju-Ha ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 8, 2012, Pages 726~736
DOI : 10.5139/JKSAS.2012.40.8.726
This paper deals with Spin/Stall Recovery Parachute System from design to ground taxiing stage which would be deployed on the high speed taxi of turbo-prop airplane. In detail design phase, design parameters- riser length, parachute type, size, porosity, parachute canopy filling time, and deployment method- were considered based on the analytical disciplines such as aerodynamics, structures, and stability & control. Before the installation of Spin/Stall Recovery System of turbo-prop airplane, all control functions of this system were validated by the SBTB(System Breakout Test Box) in the laboratory. SBTB was used to confirm if it can detect faults, and simulate the firing of pyrotechnic devices that control the deployment and jettison of it. Once confirmed normal operation, deployment of parachute on the high speed taxiing were performed.