• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.2345-2348
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• 2003

This paper deals with a problem of automatic landing guidance and control system design. The auto-landing control system for the longitudinal motion is designed in the classical PID controller. The controller gains are properly adapted to variation of the performance using fuzzy logic as a gain scheduler for the PID gains. This control logic is applied to the problem of the automatic landing control system design. From the numerical simulation using the 6DOF nonlinear model of the associated airplane, it is shown that the auto-landing maneuver is successfully achieved from the start of the flight conditions: 1500 ft altitude, 250 ft/sec airspeed and zero flight path angle.

• 제어로봇시스템학회논문지
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• 제20권11호
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• pp.1085-1091
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• 2014

This paper presents the guidance and control design for automatic carrier landing of a UAV (Unmanned Aerial Vehicle). Differently from automatic landing on a runway on the ground, the motion of a carrier deck is not fixed and affected by external factors such as ship movement and sea state. For this reason, robust guidance/control law is required for safe shipboard landing by taking the relative geometry between the UAV and the carrier deck into account. In this work, linear quadratic optimal controller and longitudinal/lateral trajectory tracking guidance algorithm are developed based on a linear UAV model. The feasibility of the proposed control scheme and guidance law for the carrier landing are verified via numerical simulations using X-Plane and Matlab/simulink.

• 한국항공운항학회지
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• 제20권1호
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• pp.86-93
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• 2012

Fuzzy control has emerged as a practical alternative to classical control schemes in controlling certain time-varying, nonlinear, and ill-defined processes. As the current of this kind of a research paradigm, we concluded that there is a need for application study of a fuzzy control theory to the flight control systems of small aircraft being to be developed at KARI. And then, this preliminary study was carried out to the automatic landing system of the canard aircraft (Firefly) for the purpose of the preparation of extension of research contents and various application areas, in which FMRLC was chosen as the fuzzy controller of the system.

• 제어로봇시스템학회논문지
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• 제15권1호
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• pp.54-60
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• 2009

In this paper, a precision landing approach is implemented based on real-time image processing. A full-scale landmark for automatic landing is used. canny edge detection method is applied to identify the outside quadrilateral while circular hough transform is used for the recognition of inside circle. Position information on the ground landmark is uplinked to the unmanned helicopter via ground control computer in real time so that the unmanned helicopter control the air vehicle for accurate landing approach. Ground test and a couple of flight tests for autonomous landing approach show that the image processing and automatic landing operation system have good performance for the landing approach phase at the altitude of $20m{\sim}1m$ above ground level.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.519-524
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• 2003

In this report, a longitudinal adaptive flight control law is presented for the automatic landing system of a Japanese automatic landing flight experiment vehicle (ALFLEX). The longitudinal adaptive flight control law is designed to track an output of the vehicle to a guidance signal from the guidance portion of the automatic landing system. The proposed adaptive control law in the attitude control portion adjusts the controller gains continuously online as flight conditions change, in spite of the existence of unmodeled dynamics. The number of the controller gains to be adjusted is decreased to 1/2 from the previous studies. Computer simulation involving six-degree-of-freedom (DOF) nonlinear flight dynamics is performed to examine the effectiveness of the proposed adaptive control law. In order to verify the influence of the dispersion of the initial conditions, the Monte Carlo simulation is also applied. The initial conditions are more widely dispersed than the previous studies. As a result, except under the unsuitable initial conditions, the ALFLEX successfully landed on the runway.

• International Journal of Aeronautical and Space Sciences
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• 제17권1호
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• pp.120-131
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• 2016

The full results of troubleshooting process related to the flight control system of a tilt-rotor type UAV in the flight tests are described. Flight tests were conducted in helicopter, conversion, and airplane modes. The vehicle was flown using automatic functions, which include speed-hold, altitude-hold, heading-hold, guidance modes, as well as automatic take-off and landing. Many unexpected problems occurred during the envelope expansion tests which were mostly under those automatic functions. The anomalies in helicopter mode include vortex ring state (VRS), long delay in the automatic take-off, and the initial overshoot in the automatic landing. In contrast, the anomalies in conversion mode are untrimmed AOS oscillation and the calibration errors of the air data sensors. The problems of low damping in rotor speed and roll rate responses are found in airplane mode. Once all of the known problems had been solved, the vehicle in airplane mode gradually reached the maximum design speed of 440km/h at the operation altitude of 3km. This paper also presents a comprehensive detailing of the control systems of the tilt-rotor unmanned air vehicle (UAV).

• 제어로봇시스템학회논문지
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• 제14권12호
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• pp.1253-1259
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• 2008

This paper presents a landing controller and guidance law for net-recovery of fixed-wing unmanned aerial vehicles. A linear quadratic controller was designed using the system identification result of the unmanned aerial vehicle. A pursuit guidance law is applied to guide the vehicle to a recovery net with imaginary landing points on the desired approach path. The landing performance of a pure pursuit guidance, a constant pseudo pursuit guidance, and a variable pseudo pursuit guidance is compared. Numerical simulation using an unmanned aerial vehicle model was performed to verify the performance of the proposed landing guidance law.

• 한국지능시스템학회논문지
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• 제25권6호
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• pp.536-541
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• 2015

본 논문은 실내에서 미니드론의 영상기반 자동 비행 및 이 착륙 제어시스템을 제안한다. 천정 카메라와 지면에 마커가 있는 환경에서 미니드론의 자동 비행 제어시스템을 구성하였다. 천장에 설치된 카메라영상을 기반으로 착륙 위치와 드론을 인식할 뿐만 아니라 드론의 움직임을 추적한다. PC서버는 드론의 위치를 계산하여 드론에 제어 명령을 전송한다. 드론의 비행 제어기는 상태 머신 기법, PID 제어와 웨이포인트-위치 제어기법을 사용하여 구현하였다. 실제 미니드론을 사용하여 제안한 자동제어시스템을 검증하였다. 바닥의 마커를 인식하여 ㄱ, ㄷ, ㅁ자 등의 특정 형상의 궤적을 따라 비행하는 것을 실험으로 확인하였으며, 높이의 차이가 있는 두 개의 착륙지점에도 착륙하는 실험에서도 우수한 성능을 보여 주었다.

• 산업융합연구
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• 제18권1호
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• pp.79-85
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• 2020

최근 원격조종과 자율조종이 가능한 무인항공기(RPAS:Remotely Piloted Aircraft System)가 택배 드론, 소방드론, 구급 드론, 농업용 드론, 예술 드론, 드론 택시 등 각 산업 분야와 공공기관에서의 관심과 활용이 높아지고 있다. 자율조종이 가능한 무인드론의 안정성 문제는 앞으로 드론 산업의 발달과 함께 진화하면서 해결해야 할 가장 큰 과제이기도 하다. 드론은 자율비행제어 시스템이 지정한 경로로 비행하고 목적지에 정확하게 자동 착륙을 수행할 수 있어야 한다. 본 연구는 드론의 센서와 GPS의 위치 정보의 오류를 보완하는 방법으로서 착륙지점 영상을 통해 드론의 도착 여부를 확인하고 정확한 위치에서의 착륙을 제어하는 기법을 제안한다. 서버에서 도착지 영상을 구글맵 API로부터 수신받아 딥러닝으로 학습하고, 드론에 NAVIO2와 라즈베리파이, 카메라를 장착하여 착륙지점의 이미지를 촬영한 다음 이미지를 서버에 전송한다. Deep Learning으로 학습된 결과와 비교하여 임계치에 맞게 드론의 위치를 조정한 후 착륙지점에 자동으로 착륙할 수 있다.

• International Journal of Aeronautical and Space Sciences
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• 제7권1호
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• pp.118-128
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• 2006

This paper deals with auto-landing guidance system design applicable to Smart UAV(Unmanned Aerial Vehicle). The proposed guidance law generates horizontal position, velocity and altitude commands in the longitudinal channel and heading angle command in the lateral channel to track a predetermined trajectory for automatic landing. The longitudinal guidance commands are derived from an approximated dynamic equations in vertical plane. These longitudinal guidance commands are appropriately distributed to each control input as the flight mode of Smart UAV is changed. The concept of VOR(VHF Omni-directional Range) guidance system is applied to generate the required heading angle commands to eliminate the lateral deviation from the desired trajectory. The performance of the proposed guidance system for Smart UAV is evaluated using the nonlinear simulation. Simulation results show that the proposed guidance system for auto- landing provides good tracking performance along the predetermined landing trajectory.