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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 41, Issue 12 - Dec 2013
Volume 41, Issue 11 - Nov 2013
Volume 41, Issue 10 - Oct 2013
Volume 41, Issue 9 - Sep 2013
Volume 41, Issue 8 - Aug 2013
Volume 41, Issue 7 - Jul 2013
Volume 41, Issue 6 - Jun 2013
Volume 41, Issue 5 - May 2013
Volume 41, Issue 4 - Apr 2013
Volume 41, Issue 3 - Mar 2013
Volume 41, Issue 2 - Feb 2013
Volume 41, Issue 1 - Jan 2013
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A Study on Real-Coded Adaptive Range Multi-Objective Genetic Algorithm for Airfoil Shape Design
Jung, Sung-Ki ; Kim, Ji-Hong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 7, 2013, Pages 509~515
DOI : 10.5139/JKSAS.2013.41.7.509
In this study, the real-coded adaptive range multi-objective genetic algorithm code, which represents the global multi-objective optimization algorithm, was developed for an airfoil shape design. In order to achieve the better aerodynamic characteristics than reference airfoil at landing and cruise conditions, maximum lift coefficient and lift-to-drag ratio were chosen as object functions. Futhermore, the PARSEC method reflecting geometrical properties of airfoil was adopted to generate airfoil shapes. Finally, two airfoils, which show better aerodynamic characteristics than a reference airfoil, were chosen. As a result, maximum lift coefficient and lift-to-drag ratio were increased of 4.89% and 5.38% for first candidate airfoil and 7.13% and 4.33% for second candidate airfoil.
Study on Tip Clearance Effect of a Counter-Rotating Ducted Fan for VTOL UAV
Min, Junho ; Ryu, Minhyoung ; Lee, Seawook ; Cho, Jinsoo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 7, 2013, Pages 516~523
DOI : 10.5139/JKSAS.2013.41.7.516
The tip clearance effect on counter-rotating ducted fan of VTOL UAV in hovering condition, was investigate using computational analysis. The
SST turbulence model is employed in this study. The numerical results of baseline model are validated by wind tunnel test in hovering and forward conditions. It is observed that if tip clearance of one rotor in the counter-rotating ducted fan increase then the thrust coefficient of another rotor increases. In Addition to this, when the tip clearance of the rear rotor increases, the thrust of the ducted fan is improved due to increasing of average total pressure at exit plane.
Rotor Track and Balance of a Helicopter Rotor System Using Modern Global Optimization Schemes
You, Younghyun ; Jung, Sung Nam ; Kim, Chang Ju ; Kim, Oe Cheul ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 7, 2013, Pages 524~531
DOI : 10.5139/JKSAS.2013.41.7.524
This work aims at developing a RTB (Rotor Track and Balance) system to alleviate imbalances originating from various sources encountered during blade manufacturing process and environmental factors. The analytical RTB model is determined based on the linear regression analysis to relate the RTB adjustment parameters and their track and vibration results. The model is validated using the flight test data of a full helicopter. It is demonstrated that the linearized model has been correlated well with the test data. A hybrid optimization problem is formulated to find the best solution of the RTB adjustment parameters using the genetic algorithm combined with the PSO (Particle Swarm Optimization) algorithm. The optimization results reveal that both track deviations and vibration levels under various flight conditions become decreased within the allowable tolerances.
Pose Estimation of Leader Aircraft for Vision-based Formation Flight
Heo, Jin-Woo ; Kim, Jeong-Ho ; Han, Dong-In ; Lee, Dae-Woo ; Cho, Kyeum-Rae ; Hur, Gi-Bong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 7, 2013, Pages 532~538
DOI : 10.5139/JKSAS.2013.41.7.532
This paper describes a vision-based only attitude estimation technique for the leader in the formation flight. The feature points in image obtained from the X-PLANE simulator are extracted by the SURF(Speed Up Robust Features) algorithm. We use POSIT(Pose from Orthography and Scaling with Iteration) algorithm to estimate attitude. Finally we verify that attitude estimation using vision only can yield small estimated error of
Surge Control of Turbofan Engine Compressor with the Variable Inlet Guide Vane
Bae, Kyoungwook ; Kim, Sangjo ; Han, Dongin ; Min, Chanoh ; Lee, Daewoo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 7, 2013, Pages 539~546
DOI : 10.5139/JKSAS.2013.41.7.539
Surge phenomenon can be occurred in a compressor when compressor performance of turbofan engine for an aircraft is changed considerably in a short time on the cases like take-off phase and changing of RPM from idle to maximum, because performance of aircraft engine is changed suddenly. This study is aimed to avoid surge in a compressor. Dynamic simulation in a compressor is modeled by simulink in specific condition. Fuel flow is control input, rpm and air mass flow are expressed in terms of transfer function. Surge margin is obtained by using compressor performance map from NPSS. VIGV(Variable Inlet Guide Vane) is controlled by PD controller with difference between surge margin and reference. Finally this paper verifies IGV can prevent surge phenomenon in a compressor.
Determination of Enthalpy in the 150kW Arc-Jet
Na, Jae Jeong ; Lee, Jeong Min ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 7, 2013, Pages 547~551
DOI : 10.5139/JKSAS.2013.41.7.547
Mass averaged and core enthalpy in the arc jet flow are obtained experimentally. The experiment is made for the 150kW Huels type arc-jet applying the test condition for the research of gasturbine engine injection cooling technique. The mass averaged enthalpy value determined by the sonic throat method is 5.5MJ/kg. The core enthalpy value determined by the heat transfer rate method is 14.3MJ/kg. Based on result of experiment, the ratio of the core to mass averaged enthalpies is 2.6.
Design, manufacturing and performance test of restorated airplane of Buhwal
Park, Chanwoo ; Kim, Byungsoo ; Cho, Taehwan ; Cho, Hwankee ; Ok, Ju Seon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 7, 2013, Pages 552~560
DOI : 10.5139/JKSAS.2013.41.7.552
Airplane Buhwal is the first light airplane which is designed and made in South Korea. Restoration of airplane Buhwal is designed based on the one made by Korean Airforce in 2004 but there are some changes also. It uses aluminum main wing, electronic indicator, BRS(Ballistic recovery parachute) and black box for improved performance. In this paper, for the restorated Buhwal, major design changes are introduced, structure, aerodynamic and stability analysis are reviewed and improved performances which is proven through flight test are shown. This study will be a big help for domestic light airplane development.
Fatigue Safe Life Analysis of Helicopter Bearingless Rotor Hub Composite Flexbeam
Kim, Taejoo ; Kee, Youngjoong ; Kim, Deog-Kwan ; Kim, Seung-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 7, 2013, Pages 561~568
DOI : 10.5139/JKSAS.2013.41.7.561
After we designed Bearingless rotor hub system for 7,000lb class helicopter, flexbeam fatigue analysis was conducted for validation of requirement life time 8,000 hours. sectional structural analysis method applying elastic beam model was used. Fatigue analysis for two sections of flexbeam which were expected to weak to fatigue damage from result of static analysis was conducted. Extension, bending and torsion stiffness of flexbeam section shape was calculated using VABS for structure analysis. S-N curve of two composite material which composed flexbeam was generated using wohler equation. Load analysis of bearingless rotor system was conducted using CAMRAD II and load analysis result was applied HELIX/FELIX standard load spectrum to generate bearingless rotor system load spectrum which was used flexbeam fatigue safe life analysis.
A Study for the Airworthiness Certification Criteria and Compliance Related to the Flight Control Law
Koh, Gi Ok ; Ko, Joon Soo ; An, Young Gab ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 7, 2013, Pages 569~576
DOI : 10.5139/JKSAS.2013.41.7.569
The Airworthiness Certification from the government has an increasingly important role due to the dramatic growth of military aircraft development industry. It is a mandatory process of qualifying the flight safety within the aircraft`s operational boundaries throughout its life cycle. The introduction of airworthiness certification has resulted in development paradigm shift from one requirement for one consumer need to the common requirement for many needs. This research paper provide the refinement of airworthiness certification criteria related to the flight control law and the verification methods which comply with its criteria.
Integrated Simulator of Airborne Multi-function Radar Resource Manager and Environment Model
Park, Jung-Woo ; Jang, Dae-Sung ; Choi, Han-Lim ; Tahk, Min-Jea ; Roh, Ji-Eun ; Kim, Seon-Joo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 7, 2013, Pages 577~587
DOI : 10.5139/JKSAS.2013.41.7.577
In this paper, an integrated radar resource manager for an airborne multi-function radar and a radar-environment simulator are presented. The radar-environment simulator includes target detection/measurement models, a nonlinear tracking filter for the airborne radar and an effective target generation algorithm. The structures and functions of modules in the radar resource manager are established and validated by the radar-environment simulator.
Operational Concept Design and Verification for Airborne SAR System
Lee, Hyon-Ik ; Kim, Se-Young ; Jeon, Byeong-Tae ; Sung, Jin-Bong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 7, 2013, Pages 588~595
DOI : 10.5139/JKSAS.2013.41.7.588
Airborne SAR system is the imaging Radar system that is loaded on a manned or unmanned aircraft, which is in charge of high quality image acquisition and moving target detection. This paper describes the operational requirements for the Airborne SAR system and suggests the operational concept to satisfy the requirements. To be specific, it describes the interface with airborne system, state definition and transition, operation mode based on mission definition file, fault management, and data storing and transmission concept. Finally, it gives the ground test results to verify the SAR system operational concept.