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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
Editor in Chief :
Volume & Issues
Volume 39, Issue 12 - Dec 2011
Volume 39, Issue 11 - Nov 2011
Volume 39, Issue 10 - Oct 2011
Volume 39, Issue 9 - Sep 2011
Volume 39, Issue 8 - Aug 2011
Volume 39, Issue 7 - Jul 2011
Volume 39, Issue 6 - Jun 2011
Volume 39, Issue 5 - May 2011
Volume 39, Issue 4 - Apr 2011
Volume 39, Issue 3 - Mar 2011
Volume 39, Issue 2 - Feb 2011
Volume 39, Issue 1 - Jan 2011
Selecting the target year
Analysis of Relations between Ice Accretion Shapes and Ambient Conditions by Employing Self-Organization Maps and Analysis of Variance
Son, Chan-Kyu ; Oh, Se-Jong ; Yee, Kwan-Jung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 8, 2011, Pages 689~701
DOI : 10.5139/JKSAS.2011.39.8.689
The relations between ambient conditions and ice accretion shapes are quantitatively analyzed by employing self-organization maps and analysis of variance. Liquid water contents(LWC), mean volumetric droplet diameter(MVD), ambient temperature and free-stream velocity are chosen as ambient conditions which change ice accretion shapes. The parameters of ice accretion shape are selected as maximum thickness, icing limits, ice heading, and ice accretion area. Qualitative analysis was conducted by employing self-organization maps which show the qualitative relations between ice shapes and ambient conditions. The quantitative results of analysis of variance yield intensity of ambient conditions to the parameters of ice accretion shapes.
Verification of the Open Source Code, OpenFOAM to the External Flows
Kim, Tae-Woo ; Oh, Se-Jong ; Yee, Kwan-Jung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 8, 2011, Pages 702~710
DOI : 10.5139/JKSAS.2011.39.8.702
This paper aims to verify the applicability of OpenFOAM, the widely recognized open source CFD code, to external flows commonly found in aeronautical problems. To this end, several representative flow cases are selected first from subsonic to supersonic flow fields. Then, the computational results obtained from OpenFOAM are systematically compared against available data from experiments and other numerical codes. It was found that the strength and location of shock are well predicted and the effects of boundary conditions on the computed results are reviewed. Subsonic flow with massive separation is selected to validate the prediction capability of OpenFOAM. Based on the current results, the limitation and possibility of OpenFOAM was confirmed and for future study using OpenFOAM was suggested.
Thermomechanical Behavior of Porous Carbon/Phenolic Composites in Pyrolysis Environments
Kim, Sung-Jun ; Han, Su-Yeon ; Shin, Eui-Sup ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 8, 2011, Pages 711~718
DOI : 10.5139/JKSAS.2011.39.8.711
The thermoelastic behavior of the porous carbon/phenolic composites is studied using the thermomechanical response model of chemically decomposing composites. The model includes thermal dependence of the porous composites, porosity in the pyrolysis process, pore pressure due to decomposing gases, and shrinkage. The poroelastic coefficients are calculated based on representative volume element model and finite element analysis. The internal stress distribution caused by pores and pore pressure, and the overall deformation are verified. The effects of the poroelastic coefficients on the thermoelastic behavior are examined through numerical experiments.
Contact Pressure of Non-Pneumatic Tires with Auxetic spokes
Kim, Kwang-Won ; Kim, Doo-Man ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 8, 2011, Pages 719~724
DOI : 10.5139/JKSAS.2011.39.8.719
A Non_Pneumatic tire (NPT) has spoke to replace air of the pneumatic tires. A NPT appears to have advantages over the conventional pneumatic tire in terms of flat proof and maintenance free. And a NPT can also be used in the space environment since it uses no air for inflation. In this study, the static contact pressure of NPTs with auxetic honeycomb spokes is investigated as a function of vertical loading and is compared with that of a pneumatic tire. The finite element based numerical simulation of the local stress of an airless tire is carried out with ABAQUS for varying vertical force and honeycomb spokes geometries.
Adaptive Control System Designs for Aircraft Wing Rock
Shin, Yoong-Hyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 8, 2011, Pages 725~734
DOI : 10.5139/JKSAS.2011.39.8.725
At high angles of attack, aircraft dynamics can display an oscillatory lateral behavior that manifests itself as a limit cycle known as wing rock. In this paper, a classical and neural network based adaptive control design methods of adaptively stabilizing the oscillatory motion by adapting uncertainties are described in detail. All methods are simulated and compared using a model for an 80o swept delta wing.
An Experimental Study of Surface Pressure on a Turbine Blade in Partial Admission
Choi, Hyoung-Jun ; Park, Young-Ha ; Kim, Chae-Sil ; Cho, Soo-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 8, 2011, Pages 735~743
DOI : 10.5139/JKSAS.2011.39.8.735
In this study, the distribution of surface pressure was measured in a steady state on a turbine blade which was moved the injected region and receded the stagnation region using a linear cascade apparatus. Axial-type blades were used and the blade chord was 200mm. The rectangular nozzle was applied and its size was
. The experiment was done at
of Reynolds number based on the chord. The surface pressures on the blade were measured at three different nozzle angles of
for off-design performance test. In addition, three different solidities of 1.25, 1.38 and 1.67 were applied. From the results, the low solidity caused the low pressure on the blade suction surface at entering region and the reverse rotating force was generated at the low nozzle angle. The positive incidence also made the pressure lower on the suction surface at entering region.
The stydy on determination method of initial optimal nozzle expansion ratio in pintle solid rocket motor
Kim, Joung-Keun ; Lee, Young-Won ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 8, 2011, Pages 744~749
DOI : 10.5139/JKSAS.2011.39.8.744
In this study, determination method of initial optimal nozzle expansion in pintle rocket was investigated. The initial optimal initial nozzle expansion was decided by maximizing the mass-averaged thrust coefficient that is calculated from thrust coefficient of minimum and maximum chamber pressure. The determination of initial optimal initial nozzle expansion was equivalent to that of the minimum propellant mass which was required for obtaining the desired mission performance. The highest pressure, thrust turndown ratio and total impulse ratio effected on the initial optimal nozzle expansion. Among them, total impulse ratio had great influence on the initial optimal nozzle expansion.
A Range-Free Localization Algorithm for Sensor Networks with a Helicopter-based Mobile Anchor Node
Lee, Byoung-Hwa ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 8, 2011, Pages 750~757
DOI : 10.5139/JKSAS.2011.39.8.750
Wireless Sensor Network is composed of a lot of sensor nodes that are densely deployed in a field. So generally this sensor nodes are spreaded using Helicopter or Fixed wing. Each node delivers own location and acquired information to user when it detects specific events. In this paper, we propose localization algorithm without range information in wireless sensor network using helicopter. Helicopter broadcasts periodically beacon signal for sensor nodes. Sensor nodes stored own memory this beacon signal until to find another beacon point(satisfied special condition). This paper develops a localization mechanism using the geometry conjecture(perpendicular bisector of a chord) to know own location. And the simulation results demonstrate that our localization scheme outperforms Centroid, APIT in terms of a higher location accuracy.
Aerodynamic and Structural Design of A High Efficiency Small Scale Composite Vertical Axis Wind Turbine Blade
Gong, Chang-Duk ; Lee, Ha-Seung ; Kim, In-Kweon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 8, 2011, Pages 758~765
DOI : 10.5139/JKSAS.2011.39.8.758
Recently, the wind energy has been widely used as a renewable energy resource due to lack and environmental issues of the mostly used fossil fuel. This work is to develop a 500W class blade design of vertical axis wind turbine system which will be applicable to relatively low speed region like Korea and for the domestic use. For this wind turbine a high efficiency and low noise turbine blade was designed with the proposing aerodynamic design procedure, and a light composite structure blade. Structural analyses were performed using the Finite Element Method and fatigue life of the designed blade is estimated. Finally, in order to check its performance, the manufactured blade was tested by using truck and the results of test was good with respect to its analysis result.
The Improvement of Tracking Accuracy of the Ground-Based Radar By the Measurement of Dynamic Attitude
Kim, Wan-Kyu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 8, 2011, Pages 766~773
DOI : 10.5139/JKSAS.2011.39.8.766
The inclination attitude of the Ground-Based Radar can be measured by the accelerometer due to its static operation environment, but the measurement error is generated from the angular acceleration of the accelerometer, which is created in mechanical oscillation by the dynamic environment, like the wind, gust, rotating antenna, etc. In this paper, the technique of reducing the measurement error of the attitude by the dynamic attitude is proposed and the result of the simulation and the analysis of tracking error by the attitude error are presented.
Day-to-Day Repeatability of the Navigation Solution and SNR from the GPS Receiver installed on KSLV-I
Kwon, Byung-Moon ; Moon, Ji-Hyeon ; Shin, Yong-Sul ; Choi, Hyung-Don ; Cho, Gwang-Rae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 8, 2011, Pages 774~787
DOI : 10.5139/JKSAS.2011.39.8.774
This paper deals with quantitative analysis about the characteristics of GNSS(Global Navigation Satellite System) signals contaminated with multipath signals and day-to-day repeatability of the navigation solution and SNR(Signal to Noise Ratio) caused by multipath signals using the collected data from GPS receiver installed on KSLV-I which was on standby on the launch pad at Naro Space Center. Since the GPS antennas, surrounding environments and GPS satellite orbits were very slightly changed with respect to the day, the repeating pattern of the solution and SNR caused by the multipath signals was verified from the collected data. Analytic result of the multipath effects and day-to-day repeatability of the navigation solution and SNR observed at the launch pad would be used for obtaining more stable performance of the GPS receiver when the satellite launch vehicles are on standby.
A Study on the Design Requirement of a Small Ring Laser Gyroscope for Medium-Grade Inertial Navigation
Kim, Cheon-Joong ; Shim, Kyu-Min ; Park, Heung-Won ; Lyou, Joon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 8, 2011, Pages 788~795
DOI : 10.5139/JKSAS.2011.39.8.788
In this paper, we present the requirements specification to develop the small ring laser gyroscope(RLG) which is applicable to the medium-grade inertial navigation system(INS) widely used as a main navigation system. To this end, first we analyse the performance specifications of RLG which is needed to configure the medium-grade INS and then we present the design results of RLG to meet the performance specifications, based on the overseas technology survey and the theoretical analysis. It is also shown in this paper what technology is required to develop a small RLG.
Performance Analysis of Self-Alignment in the Temperature Stabilizing State of Inertial Navigation System
Kim, Cheon-Joong ; Lyou, Joon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 8, 2011, Pages 796~803
DOI : 10.5139/JKSAS.2011.39.8.796
It is called self-alignment or initial alignment that INS(Inertial Navigation System) is aligned using the measurements from the inertial sensors as an accelerometer and a gyroscope and the inserted reference navigation information in the stop state. The main purpose of self-alignment is to obtain the initial attitude of INS. The accuracy of self-alignment is determined by the performance grade of the used inertial sensors, especially horizontal attitude accuracy by the horizontal accelerometer and vertical attitude accuracy by the E-axis gyroscope. Therefore the uncertain errors in the inertial sensors cause the performance of self-alignment to degrade. In this paper, we analyze theoretically and through a simulation how the errors of inertial sensors in the temperature stabilizing state, one of the uncertain errors, affect the accuracy of self-alignment.