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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 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
Side Force Modeling of Landing Gear and Ground Directional Controller Design for UAV
Cho, Sung-Bong ; Ahn, Jong-Min ; Hur, Gi-Bong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 12, 2014, Pages 997~1003
DOI : 10.5139/JKSAS.2014.42.12.997
This paper describes modeling process to obtain precise landing gear model which is necessary to design a control law for ground auto-taxi, auto take-off/landing of UAV. In this paper, landing gear side force modeling is studied to complete a landing gear model of UAV. Side force modeling is performed by calculating cornering angle including steering angle. And ground directional controller is designed by using nose wheel steering and rudder steering at the same time to control course angle error. Accuracy of landing gear side force modeling and ground directional controller is proved by comparing of auto-taxi test results with simulation results.
An Experimental Study of Acoustic Excitation Effect on Blowoff Mechanism for Premixed Flame
Shin, Jaeik ; Jeong, Chanyeong ; Yoon, Youngbin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 12, 2014, Pages 1004~1012
DOI : 10.5139/JKSAS.2014.42.12.1004
In this study, blowoff was investigated in a ducted combustor with the bluff body when acoustic excitation was forced. To observe the flame structure, OH radical chemiluminescence was used and the image was analyzed by using POD (Proper Orthogonal Decomposition) algorithm. Natural gas mainly composed of methane was used as fuel. Blowoff occurred when the equivalence ratio was reduced. Equivalence ratio causing blowoff was measured by changing air flow rate, excitation frequency and sound pressure. Blowoff equivalence ratio was varied depending on the experimental conditions. Vortex frequency behind the bluff body and resonance effect in combustor are the main factors that affect the blowoff equivalence ratios with the excitation.
Study on the Thermal Buffer Mass and Phase Change Material for Thermal Control of the Periodically Working Satellite Component
Kim, Taig Young ; Seo, Jung Gi ; Hyun, Bum-Seok ; Cheon, Hyeong Yul ; Lee, Jang-Joon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 12, 2014, Pages 1013~1019
DOI : 10.5139/JKSAS.2014.42.12.1013
Solid-liquid Phase Change Material(PCM) as a thermal control hardware for the electro-optical payload of low earth orbit satellite is numerically studied which can be substituted with Thermal Buffer Mass(TBM). The electro-optical module in LEO satellite is periodically work and high heat is dissipated during the imaging period, however, the design temperature range is very tight and sensitive. In order to handle this problem TBM is added and as a result the time constant of the module temperature increases. TBM is made of Al6010 and its mass directly affects the system design. To save the mass PCM is suggested in this study. The latent heat of melting or solidification is very high and small amount of PCM can play a role instead of TBM. The result shows that only 12% of TBM mass is enough to control the module temperature using PCM.
Suitability of Singularity Indices for Steering Law Design of Control Moment Gyros
Jin, Jaehyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 12, 2014, Pages 1020~1027
DOI : 10.5139/JKSAS.2014.42.12.1020
Singularity indices for steering law design of CMGs have been analyzed. Several qualitative criteria to evaluate the suitability of indices have been suggested. Fast calculation and consistency with the condition number of the input matrix are the most important ones. Based on these criteria, modified indices have been proposed. Properties of infinite value and finite value indices have been compared and an ad hoc method to combine those properties has been presented. Computer simulation results are given to verify the proposed method.
Boundary Layer Correction of Hypersonic Wind-tunnel Nozzle Designed by the Methods of Characteristics
Kim, So-Yeon ; Kim, Sung Don ; Jeung, In-Seuck ; Lee, Jong-Kuk ; Choi, Jeong-Yol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 12, 2014, Pages 1028~1036
DOI : 10.5139/JKSAS.2014.42.12.1028
A design procedure is established for hypersonic nozzles by using MOC(Method of Characteristics) and CFD. The inviscid nozzle contour is designed by MOC, then BLC(Boundary Layer Correction) is made by evaluating the boundary layer thickness from viscous CFD analysis. By comparing various definitions of the boundary layer thicknesses, it seems that the boundary layer thickness of 95% speed of the maximum value at the cross section satisfies best the design Mach number. Design procedure is as follow; MOC design, grid generation, inviscid analysis, viscous analysis, BLC and viscous analysis for confirmation and post-processing. All procedures are made automatically by using the batch processing.
Development of KAU Mechanical Lunar Simulants and Drop Test of Lunar Landing Gears
Yoo, Seok-Ho ; Kim, Hyun-Duk ; Lim, Jae Hyuk ; Park, Jung-Sun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 12, 2014, Pages 1037~1044
DOI : 10.5139/JKSAS.2014.42.12.1037
In this study, we designed a drop test system considering lunar surface environment and tested landing gear of experimental lunar lander. The lunar lander would be landed at soil place for soft landing. When the lunar lander touches down, the acceleration of the lander is largely affected by mechanical characteristics of the lunar soil. Accordingly, a drop test using lunar soil is needed to verify the performance of the lunar landing gear. Because the lunar soil is not available generally, we developed a lunar simulant KAUMLS(Korea Aerospace University Mechanical Luna Simulant) based on mechanical properties of the lunar soil of NASA`s LUNA PROJECT. In addition, drop tests on steel plate and dry sand are performed to evaluate impact characteristics by the surface environment.
Design to improve HUD symbol visibility in air-to-air mode
Lee, Hyuk Jun ; Choi, Jung Dong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 12, 2014, Pages 1045~1050
DOI : 10.5139/JKSAS.2014.42.12.1045
A Head-Up-Display is an avionic equipment to identify targets and flight data at same time the pilot looks over the external environment outside canopy. The HUD displays various symbols to depend on avionic mode which is composed of navigation mode, air-to-air mode, air-to-ground mode. In air-to-air mode, HUD should provide the intuitive symbols for pilot to aim the target exactly in a short time. In this paper, we propose a design method to improve the visibility of the HUD Symbols.
Launch Environment Test and Evaluation of Fuel Feeding Unit for Electric Propulsion System to Small-Satellite Applications
Kim, Younho ; Kang, Seokhyun ; Jung, Yunhwang ; Kang, Seongmin ; Seon, Jongho ; Lee, Sang-Hyun ; Cha, Won-Ho ; Eun, Hee-Kwang ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 12, 2014, Pages 1051~1056
DOI : 10.5139/JKSAS.2014.42.12.1051
A Fuel Feeding Unit of electric propulsion system has been developed for the small-satellite applications. The fuel feeding unit stores the xenon gas with high pressure and density as a fuel. Xenon can affect to system stability since xenon has the transient condition under the critical point which is in ambient temperature on the launch environment. The functional and structural stability on the launch environment needs verification through the ground tests. The design points and verification tests of the system were discussed and test results were described on this text. The system stability on the launch environment was verified through these verification tests.
GaInP/GaAs/Ge Triple Junction Solar Array Power Performance Evaluation on Geostationary Orbit
Koo, Ja-Chun ; Park, Hee-Sung ; Lee, Na-Young ; Cheon, Yee-Jin ; Cha, Han-Ju ; Moon, Gun-Woo ; Ra, Sung-Woong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 12, 2014, Pages 1057~1064
DOI : 10.5139/JKSAS.2014.42.12.1057
The satellite on geostationary orbit accommodates multiple payloads into a single spacecraft platform and launched in June 26, 2010. The electrical power required to the satellite during sunlight is generated by a solar array wing. The solar cells are the GaInP/GaAs/Ge Triple Junction cells named Gaget2 cells from RWE Space, which were based on a Spectrolab epitaxy. This paper evaluates solar array power performance at end of design life based on the trend analysis results for the flight data on geostationary orbit. The estimated solar array power performance at end of design life compares with the power performance provided by solar array manufacturer. The solar cells show nominal behavior without significant degradation through the trend analysis results.
Implementation of a spaceborne GPS signal processing device and its performance analysis
Jin, Hyeun-Pil ; Park, Seong-Baek ; Kim, Eun-Hyouek ; Yun, Ji-Ho ; Lee, Hyun-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 12, 2014, Pages 1065~1072
DOI : 10.5139/JKSAS.2014.42.12.1065
We developed a GPS digital signal processing FPGA IP, SIGP-1001 to replace the obsolete GP2021 device, which has been used for many space-borne GPS receivers. From a series of tests, we verified that SIGP-1001 has equivalent performance to the GP2021 device under the same operating condition and concluded that SIGP-1001 can replace the GP2021 device. The reliability of a GPS receiver can be improved by using a space-grade FPGA with SIGP-1001 instead of the GP2021 device and its performance is expected to be improved by increasing the number of search channels.
A Study on Certification Procedures for Aircraft Parts Manufacturer Approval
Lee, Kang-Yi ; Yi, Baeck-Jun ; Chung, Ha-Girl ; Ryoo, Chang-Kyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 12, 2014, Pages 1073~1079
DOI : 10.5139/JKSAS.2014.42.12.1073
Aircraft parts are considered as a significant element for the continued airworthiness of the certified aircraft well as a partial component consisting of the new aircraft design. US FAA established the certification system of Parts Manufacturer Approval in 1965, which is contributing to the continued airworthiness of the aircraft in operation and to the expansion of worldwide market of aircraft parts. In this paper, we compared the differences of the certification systems between FAA Parts Manufacturer Approval and EASA European Part Approval, and proposed the rulemaking items to improve Korean Parts Manufacturer Certification System and to contribute to growth of aircraft parts industry.