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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 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
Selecting the target year
A development of an Optimization-Based Flight Scheduler and Its Simulation-Based Application to Real Airports
Ryu, MinSeok ; Song, Jae-Hoon ; Choi, Seongim ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 9, 2013, Pages 681~688
DOI : 10.5139/JKSAS.2013.41.9.681
Several problems caused by inevitable increment of airplane have been issued. The most effective solution to solve the issues is considered as establishing appropriate Air Traffic Management (ATM) that reduces aircraft`s delay at an airport and intensify the airport`s capacity. The purpose of this paper is to produce the optimum aircraft schedules that maximize the aircraft throughput by smooth air traffic flow near terminal area of an airport In this paper, mathematical formulations of the scheduling problem are firstly specified. Based on the mathematical modelling, an Optimization-Based Flight Scheduler that provides the optimum flight schedules for arriving aircraft is developed by introducing the Mixed Integer Linear Programming(MILP) and the Genetic Algorithms(GA). With this scheduler, we calculated the optimum schedules to compare to real schedule data from an Incheon Airport. As a result, it is validated that aircraft throughput produced by the optimum schedule is much better than that of the schedule from the Incheon airport. The optimization-based flight scheduler is expected to deal with problems due to the aircraft saturation in near future.
Data Quality Analysis of Korean GPS Reference Stations Using Comprehensive Quality Check Algorithm
Kim, Minchan ; Lee, Jiyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 9, 2013, Pages 689~699
DOI : 10.5139/JKSAS.2013.41.9.689
During extreme ionospheric storms, anomalous ionospheric delays and gradients could cause potential integrity threats to users of GNSS (Global Navigation Satellite System) augmentation systems. GNSS augmentation ground facilities must monitor these ionospheric anomalies defined by a threat model and alarm the users of safely-of-life applications within time-to-alerts. Because the ionospheric anomaly threat model is developed using data collected from GNSS reference stations, the use of poor-quality data can degrade the performance of the threat model. As the total number of stations increases, the number of station with poor GNSS data quality also increases. This paper analyzes the quality of data collected from Korean GPS reference stations using comprehensive GNSS data quality check algorithms. The results show that the range of good and poor qualities varies noticeably for each quality parameter. Especially erroneous ionospheric delay and gradients estimates are produced due to poor quality data. The results obtained in this study should be a basis for determining GPS data quality criteria in the development of ionospheric threat models.
Experimental Analysis of a Supersonic Plasma Wind Tunnel Using a Segmented Arc Heater with the Power Level of 0.4 MW
Kim, Min-Ho ; Lee, Mi-Yeon ; Kim, Jeong-Soo ; Choi, Chea-Hong ; Seo, Jun-Ho ; Moon, Se-Yeon ; Hong, Bong-Guen ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 9, 2013, Pages 700~707
DOI : 10.5139/JKSAS.2013.41.9.700
Experimental analyses on a supersonic plasma wind tunnel of CBNU (Chonbuk National University) were carried out. In these experiments, a segmented arc heater was employed as a plasma source and operated at the gas flow rates of 16.3 g/s and the total currents of 300 A. The input power reached ~350 kW with the torch efficiency of 51.4 %, which is defined as the ratio of total exit enthalpy to the input power. The pressure of plasma gas in the arc heater was measured up to 4 bar while it was down to ~45 mbar in a vacuum chamber through a Laval nozzle. During this conversion process, the generated supersonic plasma was expected to have a total enthalpy of ~11 MJ/kg from the measured input power and torch efficiency. In addition to the measurement of total enthalpy, a cone type probe was inserted into the supersonic plasma flow in order to estimate the angle between shock layer and surface of the probe. From these measurements, the temperature and the Mach number of the supersonic plasma were predicted as ~2,950 K and ~3.7, respectively.
Empennage Design of Solar-Electric Powered High Altitude Long Endurance Unmanned Aerial Vehicle
Hwang, Seung-Jae ; Lee, Yung-Gyo ; Kim, Cheol-Wan ; Ahn, Seok-Min ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 9, 2013, Pages 708~713
DOI : 10.5139/JKSAS.2013.41.9.708
KARI is developing a solar-electric powered HALE UAV(EAV-3). For demonstrating the technology, EAV-2H, a down-scaled version of EAV-3, is developed and after EAV-2H`s initial flight test, the directional stability and control need to be improved. Thus, the vertical tail and rudder of EAV-2H are redesigned with Advanced Aircraft Analysis(AAA). Size of the rudder is increased from mean chord ratio of rudder to vertical tail, $C_r/C_v(%)
Design and Test of an Assembly of Air Intake and Variable Geometry Inertial Separator for a Turboprop Aircraft
Kim, Woncheol ; Oh, Seonghwan ; Lee, Sanghyo ; Park, Jonghwa ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 9, 2013, Pages 714~719
DOI : 10.5139/JKSAS.2013.41.9.714
A turboprop aircraft for this study is required to operate at icing condition in order that it performs its given mission. So an air intake system of the turboprop aircraft should be designed and verified not only to provide the maximum possible total pressure at engine inlet at normal flight condition, but also to include an inertial separator which protects Foreign Object Debris (FOD) like ice or snow at icing condition from entering into the engine inlet screen which can cause or lead an catastrophic engine failure like engine flame-out or severe damage. So an air intake assembly incorporating a variable geometry inertial separator has been designed and then CFD/structural analysis for the assembly was performed to see its design results. Then 35% scaled model of the air intake assembly was manufactured and wind tunnel test was done. This paper describes the detailed design results for the aerodynamic design, analysis and wind tunnel testing during the development process of the air intake assembly.
Structural Design of Cube Satellite by Using Heating Wire Cutting Type Separation Mechanism
Oh, Hyun-Ung ; Kwon, Sung-Cheol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 9, 2013, Pages 720~725
DOI : 10.5139/JKSAS.2013.41.9.720
Nylon wire cutting method by nichrome wire is generally applicable for cube satellite applications due to its advantages of simplicity. However, the system complexity is not avoidable to apply it on the cube satellite with multi-deployable structures. A lower constraint force of the mechanism is also one of the disadvantages of the mechanism. In this study, we proposed a preliminary structure design of cube satellite with the separation mechanism which is applicable for holding and release of the multi-deployable structures. The effectiveness of the mechanism design was verified through function test of EM mechanism. The structure analysis results showed that the structure design proposed in this study is feasible.
Comparisons of Rotor Performance and Noise between Candidate Light Civil Helicopters
Chung, Kihoon ; Kang, Hee Jung ; Kim, Do-Hyung ; Yun, Chul Yong ; Kim, Seungho ; Park, Kuhwan ; Lee, Sang-Gi ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 9, 2013, Pages 726~733
DOI : 10.5139/JKSAS.2013.41.9.726
The rotor blade of helicopter is the core component determining helicopter performance and requiring low noise and low vibration because the blade becomes the major source of noise during flight. The performance analysis of candidates rotor blades is very critical because LCH(Light Civil Helicopter) will be developed parallel with LAH(Light Armed Helicopter) as an international upgrade program based on the existing platform of foreign civil helicopter. This research was aimed to recognize the performance of the candidates rotor blades compared with the newly developed foreign rotor blades and to investigate the feasibility about developing korea unique shape rotor blades by analysis the rotor performance and noise. The result of this research can be used for the target performance index during negotiation with foreign helicopter company and developing korea unique shape rotor blades.
Review on U.S. Army Helicopter Mishap Analysis for Revision of Crashworthiness Requirements
Hwang, Jungsun ; Lee, Sangmok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 9, 2013, Pages 734~739
DOI : 10.5139/JKSAS.2013.41.9.734
Representative crashworthiness requirement documents for military helicopter are MIL-STD-1290 and the Aircraft Crash Survival Design Guide(ACSDG) which were lastly revised in the 1980`s. Taking analysis results of diverse U.S. Army helicopter mishaps into account, we can say that adequate guidelines do not exist to ensure crashworthiness of new generation aircraft. In this paper, U.S. Army helicopter mishap analysis conducted by U.S. Army Research, Development and Engineering Command(RDECOM) is readjusted to review the basis of new crashworthiness design criteria for military helicopter, in other words, Full Spectrum Crashworthiness Criteria(FSCC). This analysis effort is a part of FSC development. This effort was to research and quantify the dynamics of military aircraft crashes to be used as the quantitative basis for new design criteria.
A Study on the Emphasis of Human Tolerance in the Crash Event
Hwang, Jungsun ; Lee, Sangmok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 9, 2013, Pages 740~746
DOI : 10.5139/JKSAS.2013.41.9.740
Design with crashworthiness concept has been emphasized for almost aircraft and motor vehicles. However, crashes accompanied serious injury and death have been continuously occurred, and will be occurred subsequently. What was worse, it is a well-known fact that there were a good many crashes classified as survivable accidents in which fatal injuries were reported. But we cannot say that fatal injuries were inevitable consequences of those crashes. If crashworthy design for seat, restraint systems, and cabin strength were adequate or right, survivability in a crash event could be maximized greatly. To substantiate the right crashworthiness, we must thoroughly understand the characteristics of human tolerance under abrupt acceleration change, and the cabin design should be combined with proper use of energy absorbing technologies that reduce accelerations experienced by the occupants. In this paper, the emphasis on the human tolerance under abrupt accelerations as well as the necessity of change in design requirements for crash environment will be stressed to widen the belt of consensus for the right crashworthy design.
Development of Integrated Test Equipment for Airborne SAR System and Control Unit
Lee, Hyon-Ik ; Hwang, Tae-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 9, 2013, Pages 747~754
DOI : 10.5139/JKSAS.2013.41.9.747
This paper describes SCTE(System and Control unit Test Equipment) as an integrated test equipment for airborne SAR system and control unit. SCTE enhances reusability of test equipment by modular design for required functions and strengthens automatic testing and test convenience by providing functions such as script-based testing function and report generation function. Also, it includes a navigation data simulator which can simulate various flight conditions. In this paper, we details SCTE requirements, H/W and S/W design, implementation, and test results with control unit and SAR system.
Study on the EMC analysis and test results of the digital channel amplifier considering space Environment
Hong, Sang-Pyo ; Jin, Byeong-Il ; Jin, Bong-Cheol ; Seo, Hak-Keum ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 9, 2013, Pages 755~760
DOI : 10.5139/JKSAS.2013.41.9.755
The electromagnetic compatibility and its effects, and the system design considerations in space environment are studied in this paper using Multipator. The system level EMC test results of digital channel amplifier(DCAMP), its affects upon the H/W improving methods regarding its over exceed value of EMC specification are discussed. These analysis values and test results can be used as the criteria for the selection of EMC requirements and of the MILSATCOM system design.