• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.12
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• pp.997-1003
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• 2014

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.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.28 no.2
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• pp.29-35
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• 2020

In this paper, we established a prediction model of fuel consumption at the aircraft's taxi operation. To look for countermeasures to reduce fuel consumption and carbon emissions, Airbus A380's actual ground taxi data was used. As a result, the number of stops or turnings during the taxi operation was not related to fuel consumption. It was confirmed that the amount of fuel consumption in the taxi operation was the taxi time and the thrust change. It can be confirmed that ground control optimization, which is the result of close cooperation between the control organization and the airline, is absolutely necessary to reduce taxi time and minimize the occurrence of thrust change events.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.1
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• pp.46-53
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• 2017

This paper shows a length of wirecutter using an analysis based on Rotorcraft's control input and taxiing speed. In case of selecting an inappropriate length of wirecutter which applies to rotorcraft for safety, this causes a collision between blade and wirecuter, or an accident by wire. We review the control input which was used in development stage, and establish the conditions of control input which are needed in taxiing. Based on these conditions, we review the collision possibility between blade and wirecutter through analysis in case of 20, 40, 60 kts taxiing speed. Following, this result is verified by comparison with that of a simulation test in rotorcarft. Finally, in case of high collision possibility, we presented the downsize length to avoid the collision and increment of non-protective area in flight, simultaneously.

• Journal of Advanced Navigation Technology
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• v.20 no.3
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• pp.167-174
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• 2016

Runway and taxiway is base facilities for aircraft take off and landing and runway capacity is one of major factor for airport capacity. Runway occupancy time is affect on the runway capacity. The identification of aircraft using taxiway by analysis of airport ground surveillance data and the measurement of pass time on the points is general method for the confirmation of the runway occupancy time. This study is runway occupancy time analysis of landing airplane using ADS-B message, in this study we surveyed landing aircraft runway occupancy time and analysis of serviced record using taxiway include rapid exit taxiway. The result of analysis is to confirm the different of landing direction and aircraft category on the same runway caused by structure of airport. Also the result of runway occupancy time analyzed data, it is base input data for the air transportation simulation.

• Journal of Aerospace System Engineering
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• v.11 no.6
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• pp.17-25
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• 2017

Vertical reaction force between ground and tire is an important parameter determining the ground behavior characteristics of aircraft. This parameter can be used to calculate the lateral force and friction. However, it is hard to obtain this parameter in real-time when the aircraft is taxiing. Therefore, pre-analysis of ground behavior and vertical reaction force should be conducted using ground simulation results to prevent rollover or hazardous scenarios. In this paper, a Landing Gear and Full-Aircraft model was constructed using VI-Aircraft S/W. The roll behavior of aircraft was analyzed using steering simulation results compared with taxi-test data.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.8
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• pp.726-736
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• 2012

This paper deals with Spin/Stall Recovery Parachute System from design to ground taxiing stage which would be deployed on the high speed taxi of turbo-prop airplane. In detail design phase, design parameters- riser length, parachute type, size, porosity, parachute canopy filling time, and deployment method- were considered based on the analytical disciplines such as aerodynamics, structures, and stability & control. Before the installation of Spin/Stall Recovery System of turbo-prop airplane, all control functions of this system were validated by the SBTB(System Breakout Test Box) in the laboratory. SBTB was used to confirm if it can detect faults, and simulate the firing of pyrotechnic devices that control the deployment and jettison of it. Once confirmed normal operation, deployment of parachute on the high speed taxiing were performed.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.17 no.4
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• pp.32-41
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• 2009

This paper presents the work being carried out in order to reduce the ground turbulence by the fence in the vicinity of airport runway. In preliminary study, we knows that cross-wind effect in the vicinity of runway is highly dependent on the shape of the buildings and have predicted results confirmed reduction of wind-effect by doing that set up the building with a fence, terraced shape or gap. This study is to figure out effect of ground turbulence by the building with fence, which is changing fence height, in using two-dimensional computational fluid dynamics analysis.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.5 no.1
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• pp.65-79
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• 1997

In this study, we deviced side warning system that is necessary to the ground operation of aircraft. The system consist of obstacle detection part, transmission part, receive part, and warning part. We used TOF(Time Of Flight) method using 40kHz ultrasonic wave as the obstacle detection part. The 447MHz RF module was applied to the transmission and receive part. The warning part is activated by the computer using received distance data. The detection system attach to the left/right side edge of main wing and horizontal stabilizer. We have decided 10m obstacle detection range. The result of experiment was satisfactory.

• Current Industrial and Technological Trends in Aerospace
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• v.7 no.2
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• pp.115-120
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• 2009

Description in this paper is a system for new range measurement method between an aircraft and runway with circular mark in landing runway. The system includes an altimeter and a camera installed on the aircraft, and a circular mark placed on a landing runway. The camera installed on the aircraft must be oriented toward in front of the aircraft, and configured to detect the shape of the circular mark in image information form and a flight control computer configured to calculate the angle between the aircraft and the ground, the ground range between the aircraft and the circular mark, and the slant range between the aircraft and the circular mark with the altitude information measured by the altimeter. This system configured to control the automatic landing of the aircraft with this information.

• Current Industrial and Technological Trends in Aerospace
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• v.4 no.2
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• pp.68-75
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• 2006

항공기용 타이어는 지상에 있는 경우에 항공기의 중량을 견뎌야 하고, 활주 및 착륙 과정에서는 열발생 및 마모에 견디면서 탑승객에게 안정감과 안락함을 제공할 수 있어야 한다. 따라서 타이어 구조는 항공기 하중뿐 아니라 높은 각속도에서 발생하는 작용력을 견뎌야 하며 착륙시에는 브레이크에 의한 높은 동적 제동하중을 지면에 전달하는 동시에 지면과의 충돌충격을 흡수할 수 있는 능력이 요구된다. 이러한 모든 기능은 타이어의 수명기간동안 신뢰성 있게 유지되어야 한다. 현재 항공기에 사용되는 타이어는 바이어스 타이어가 주류를 이루고 있지만 최근 개발되는 신규 항공기를 중심으로 래디얼 타이어의 사용이 증가하고 있다. 이러한 최신의 산업동향을 반영하여 항공기용 타이어에 대한 안전기준이 보완되고 있다. 본 글에서 항공기용 타이어에 대한 기술표준품표준서를 기준으로 최신 인증기술동향에 대하여 고찰하고자 한다.