• 항공우주시스템공학회지
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• 제3권3호
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• pp.13-16
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• 2009

Aircraft flight control surfaces which are one of the most important elements of safety allow a pilot to adjust and control the aircraft's flight attitude. This paper is described of the control surface deflection angle measuring device. Data analysis through ground test and flight test can provide reliability of this device using the present system. It is also shown that measuring system is capable of detecting failure of control surfaces.

• 제어로봇시스템학회논문지
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• 제12궈1호
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• pp.78-84
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• 2006

This paper describes UAV (Unmanned Aerial Vehicle) control system which employs PC104 modules. It is controlled by application program based on Linux OS. This application consists of both Linux device driver in kernel-space and user application in user-space. In order to get data required in the unmanned flight, external devices are connected to PC104 modules. We explain how Linux device drivers deal with data transmitted by external devices and we account for how the user application controls UAV on the basis of data processed in the device driver as well. Furthermore we look into the role of GCS (Ground Control Station) which is to monitor the state of UAV.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1997년도 한국자동제어학술회의논문집; 한국전력공사 서울연수원; 17-18 Oct. 1997
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• pp.1655-1658
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• 1997

To obtain aircraft dynamic parameters, various estimation methods such as Maximum Likelihood, Linear Regression are applied. In this paper we adopt the extended Kalman filter(EKF) to estimate the stability and control derivatives in aircraft dynamic models from flight test data. The extended Kalman filter is applied to nonlinear augmented system assuming that unknown parameters are additional states. In this work, the results of the extended Kalman filter are compared with the results of the wind tunnel test using Chang Gong-91 aircraft flight test data.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1993년도 한국자동제어학술회의논문집(국내학술편); Seoul National University, Seoul; 20-22 Oct. 1993
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• pp.185-188
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• 1993

The goal of this paper is to develop an on-board controller for a model helicopter's hovering attitude control, using i8096 one-chip microcontroller. Required controller algorithm is programmed in ASM-96 assembly language and downloaded into an i8096 microcontroller. The performance of hovering flight using this system is verified by experiments with the model helicopter mounted on an instrumented flight stand where 3 potentiometers and an optical proximity sensor measure te attitude and main rotor speed of the helicopter.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2001년도 ICCAS
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• pp.141.3-141
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• 2001

Since 1990´s, there has been many researches for the development of the Unmanned Aerial Vehicle (UAV). Especially, for the development of digital electronics, the technologies of UAV toward to the miniaturization low-cost, and high reliability. Therefore, recent trends for the development of UAV are focused on the development modern Flight Control System (FCS). In this paper, focusing on the FCS, the development process for Sejong Unmanned Research Vehicle -1 (SURV-1) from design to flight test is presented.

• 한국시뮬레이션학회논문지
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• 제13권2호
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• pp.45-52
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• 2004

This paper presents a prototype visualization system of mixed reality for a VR flight simulator. The chroma key technique is used to build the mixed reality model for a VR flight simulator. The Daedeok science town can be visualized in real time according to the rider control. He can also see his own hand/foot operating the control stick/rudder as well as virtual environment projected to the blue-screen using a video-see-through HMD.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2002년도 ICCAS
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• pp.40.2-40
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• 2002

This paper presents the reconfigurable flight controller in the presence of jammed actuator fault using the adaptive sliding mode control scheme. It is developed under the assumption that the control surface fault cannot be detected and the positions of stuck control surfaces are unknown. It is well known that sliding mode controller shows good performance for the systems with various uncertainties. None-operating stuck actuator makes the system behave like bias which degrades the system performance and sometimes destabilizes the system. Therefore, the bias term generated by actuator faults has to be compensated by the control system. To the objective, we adopt the adaptive sliding mode cont...

• 한국항공운항학회지
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• 제30권4호
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• pp.92-97
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• 2022

In the Aviation Safety Act, the part about fatigue management of Flight dispatcher was added as an amended law. Prior to the amendment of the Act, the regulations on fatigue of flight dispatcher governed by the FOM approved and reported by airlines according to the Ministry of Land, Infrastructure and Transport, but were enforced by law from June 9, 2021. In this study, the scope and work type of flight dispatchers are checked, and unlike flight attendants, it is intended to consider legal working hour management measures for flight dispatchers according to the enforcement of the fatigue management act.

• 한국컴퓨터정보학회논문지
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• 제13권4호
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• pp.221-230
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• 2008

본 논문은 현재 사용하고 있는 비행정보 시스템 전체를 연구하고 차세대 유비쿼터스 비행정보시스템을 설계하였다. 지상의 서비스에서 좌석예약, 운송, 발권과 수화물 역추적, 그리고 비행기 내에서 고객을 위한 AVOD, 게임, TV, 휴대전화, 기내 인터넷 사용과 항공사와 관제업무인 ATC, ATS, 항공교통관제업무에 대한 유비쿼터스 비행정보시스템을 연구하였다. 연구 결과를 토대로 하여 차세대 유비쿼터스 비행정보시스템과 네트워크 보안, 시스템 보안에 필요한 정보보호 시스템을 설계하였으며, 기존의 유비쿼터스 비행정보시스템과 차세대 시스템을 비교 분석하여 개선점과 차이점을 도출하였다. 본 논문의 연구결과 세계 항공 및 관련산업에 비전을 제시하고 통신효율성과 고객의 만족도 및 비행 안전성과 효율성을 확보하여 비행정보산업에 새로운 지평을 개척할 것이다.

• Advances in aircraft and spacecraft science
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• 제1권3호
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• pp.353-378
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• 2014

This paper deals with the early development of the Anuloid, an innovative disk-shaped VTOL aircraft. The Anuloid concept is based on the following three main features: the use of a ducted fan powered by a turboshaft for the lift production to take-off and fly; the Coanda effect that is developed through the circular internal duct and the bottom portion of the aircraft to provide further lift and control capabilities; the adoption of a system of ducted fixed and swiveling radial and circumferential vanes for the anti-torque mechanism and the flight control. The early studies have been focused on the CFD analysis of the Coanda effect and of the control vanes; the flyability analysis of the aircraft in terms of static performances and static and dynamic stability; the preliminary structural design of the aircraft. The results show that the Coanda effect is stable in most of the flight phases, vertical flight has satisfactory flyability qualities, whereas horizontal flight shows dynamic instability, requiring the development of an automatic control system.