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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 42, Issue 12 - Dec 2014
Volume 42, Issue 11 - Nov 2014
Volume 42, Issue 10 - Oct 2014
Volume 42, Issue 9 - Sep 2014
Volume 42, Issue 8 - Aug 2014
Volume 42, Issue 7 - Jul 2014
Volume 42, Issue 6 - Jun 2014
Volume 42, Issue 5 - May 2014
Volume 42, Issue 4 - Apr 2014
Volume 42, Issue 3 - Mar 2014
Volume 42, Issue 2 - Feb 2014
Volume 42, Issue 1 - Jan 2014
Selecting the target year
Experimental study of structural protection performance of Y
Ryu, Suk-Kyu ; Yang, Do-Chul ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 4, 2014, Pages 279~283
DOI : 10.5139/JKSAS.2014.42.4.279
In the present paper, the physical and chemical resistance to Fluorine of ceramic coating materials (
) were studied.
specimens coated by thermal plasma spray were tested inside Fluoro-carbon plasma chamber, and their resistance performance to Fluorine was compared. From the comparison, it was verified that ZrO-
has physically and chemically stronger resistance to Fluorine than
. This characterization about the physical and chemical resistance of coating materials can be applied to provide further insights on how to optimize the coating material and engineer the chamber design for future technology.
Optimization of shock absorption system for lunar lander considering the effect of lunar regolith
Yang, Soon Shin ; Kang, Yeon Chul ; Son, Jae Yeon ; Oh, Min Hwan ; Kim, Jeong Ho ; Cho, Jin Yeon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 4, 2014, Pages 284~290
DOI : 10.5139/JKSAS.2014.42.4.284
To successfully explore the moon by lunar lander, it is essential to guarantee the safe landing of lunar lander. Therefore, efficient shock absorption system of lunar lander should be designed in order to reduce landing impact force. Also, for more practical design of lunar lander, it is important to consider the effect of lunar regolith. In the line of thought, finite element model of lunar lander considering the effect of lunar regolith is developed. To reduce landing impact force, optimization of shock absorption system for lunar lander has been carried out. In optimization, sequential approximate optimization method based on meta-model is used. Through the result of optimization, it is verified that landing impact force on lunar lander can be efficiently reduced by the present optimization procedure.
Experimental Investigations of Accuracy Improvement in Wind Tunnel Testing Using Design of Experiments
Oh, Se-Yoon ; Park, Seung-O ; Ahn, Seung-Ki ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 4, 2014, Pages 291~297
DOI : 10.5139/JKSAS.2014.42.4.291
A Design of Experiments(DOE) approach to an experimental study of fuselage drag and stability characteristics of a helicopter configuration was applied to achieve an accuracy improvement in the wind tunnel testing. The impact of blocking the test was assessed by comparing the ANOVA table for the blocked and unblocked cases. For a second-order response model, the role of blocking resulted in a substantial increase in the accuracy of test results. These accuracy improvement could be achieved through randomization, blocking, and replication of the data points i.e. a re-ordering of the test sequence where the data were acquired.
Analysis of the Influence of Ground Effect on the Aerodynamic Performance of a Wing Using Lifting-Line Method
Lee, Chang Ho ; Kang, Hyung Min ; Kim, Cheolwan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 4, 2014, Pages 298~304
DOI : 10.5139/JKSAS.2014.42.4.298
The lifting-line method based on Weissinger`s method is extended to be able to analyze the ground effect. The method is applied to predict the variation of aerodynamic performance due to ground effect for the elliptic wing with aspect ratio of 10 and the wing of human powered aircraft. While the vortex strength of the wing increases slightly, the downwash decreases significantly as the wing approaches to the ground. For the wing of human powered aircraft, the increment of lift at the height of 2m is 5% than the lift outside the influence of ground effect. The decrease of induced drag at the height of wing span is 10% and at the height of 2m is 55% than that out of ground effect.
System Modeling and Waypoint Guidance Law Designing for 6-DOF Quadrotor Unmanned Aerial Vehicle
Lee, Sanghyun ; Kim, Youdan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 4, 2014, Pages 305~316
DOI : 10.5139/JKSAS.2014.42.4.305
As avionics and mechanical devices have been developed, the size of unmanned aerial vehicle (UAV) is getting smaller. However, the complicated and accurate missions are provided to the UAV. Among various types of UAVs, quadrotors are widely used for their availability by virtue of simple structure and hovering function. However, the control of quadrotor is highly constrained, because the quadrotor is an under-actuated system which has only 4 actuator inputs. To deal with this under-actuated problem, a new quadrotor model with two more actuators in addition to the 4 propeller inputs is provided to make the system fully-actuated. For the proposed model, a controller is designed using feedback linearization methods. To validate the model and to verify the performance of the proposed controller, numerical simulation is performed.
Homing Loop Design for Missiles with Strapdown Seeker
Hong, Ju-Hyeon ; Ryoo, Chang-Kyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 4, 2014, Pages 317~325
DOI : 10.5139/JKSAS.2014.42.4.317
For a missile with a strapdown seeker, line-of-sight rate for guidance is obtained by compensating the look angle rate from the strapdown seeker by the body angular rate from rate gyros. However, the body angular rate from rate gyros has different signal properties when it compared to the body angular rate implicitly included in the look angle rate. Typically this discrepancy causes instability of homing loop. In this paper, we propose a design method of homing loop where seeker delay is compulsively placed in the output signal of the rate gyros for accordance of both body rates. Also, PID control loop is considered for obtaining stabilized guidance command even though uncertainties of seeker delay is associated. The stability analysis for the linear homing loop before and after the compensation has been done. The stability and performance of the designed terminal homing loop is verified through full nonlinear 6-DOF simulations.
Aerodynamic Characteristics Analysis of Small Two-Stage Turbo Blower Using CFD
Seo, Seungjae ; Ryu, Minhyoung ; Cho, Leesang ; Cho, Jinsoo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 4, 2014, Pages 326~335
DOI : 10.5139/JKSAS.2014.42.4.326
Aerodynamic characteristics of the small two-stage turbo blower were investigated using commercial CFD tool(ANSYS CFX Ver. 14.5) in this paper. Turbo blower, which is a centrifugal type of turbomachinery, is used in various industries. It is used for application that required high static pressure rising at relatively small volumetric flow rate. In order to understand the mechanism of static pressure rising, the aerodynamic characteristics of the small two-stage turbo blower are analyzed at high rotating speed in this study. The k-
SST turbulence model, which is good at prediction of adverse pressure gradient flows, was applied. The CFD results of the turbo blower are validated by performance test. The static pressure rising of the turbo blower is nonlinearly increased over the first stage and the second stage. The secondary flow occurred at guide vanes, between the casing and the first impeller shroud, and the bottom of the impeller disk. As a result, It is required that whole fluid area is analyzed to predict aerodynamic characteristics of small two-stage turbo blower. and the result should be selected with considering for error from experiment and CFD.
The Study of Advanced Propeller Blade for Next Generation Turboprop Aircraft -Part II. Static Structural Design and Test
Choi, Won ; Park, Hyun-Bum ; Kong, Chang-Duk ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 4, 2014, Pages 336~343
DOI : 10.5139/JKSAS.2014.42.4.336
Modern advanced-turboprop propellers are required to have high structural strength to cope with the thrust requirement at high speed. The high stiffness and strength carbon/epoxy composite material is used for the major structure and skin-spar-foam sandwich structural type is adopted for advantage in terms of the blade weight. As a design procedure for the present study, the structural design load is estimated through investigation on aerodynamic load and then flanges of spars from major bending loads and the skin from shear loads are sized using the netting rule and Rule of Mixture. In order to investigate the structural safety and stability, stress analysis is performed by finite element analysis code MSC. NASTRAN. It is found that current methodology of composite structure design is a valid method through the static structural test of prototype blade.
A Study on Improvement about abnormal display of Multi Function Display for KUH
Kim, Young Mok ; Chang, Joong Jin ; Jun, Byung Kyu ; Kim, Chang Young ; Kim, Tae Hyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 4, 2014, Pages 344~350
DOI : 10.5139/JKSAS.2014.42.4.344
Multi Function Display(MFD) of Korean Utility Helicopter(KUH) is the component of mission management/display control system and displays image information(navigation, flight, survivability, digital map, maintenance) acquired from Mission Computer(MC) while the aircraft is operated. It is an essential equipment for pilots to perform flight mission and it has functions of display scene control, data display, built in test(BIT) and brightness control. In this paper, it is analyzed the cause of abnormal display(flickering) on MFD and summarized the design changes to solve the defect. It is also described system safety analysis and suggested verification results of flight/ground test.
Space Qualification of Small Satellite Li-ion Battery System for the Secured Reliability
Park, Kyung-Hwa ; Yi, Kang-Hyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 4, 2014, Pages 351~359
DOI : 10.5139/JKSAS.2014.42.4.351
This paper introduces the lithium ion battery system for LEO(Low Earth Orbit) small satellites. This study proves the reliability of lithium ion batteries applying to the space application. The specifications for lithium ion battery unit are proposed to supply power to the satellite and the overall mechanical design including structural simulation to confirm the reliability of the lithium ion BMS(Battery Management System) under the space environment and launching conditions. The results of structural simulation, functional tests, and space environmental tests show the lithium ion battery system is space qualified. Space qualification of the small satellite battery system to secure reliability of BMS and lithium ion batteries lend credibility for using lithium ion batteries in space application.