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Decentralized Phase Angle Control for Standoff Tracking using Multiple Unmanned Aircraft
Seungho Yoon,Youdan Kim 제어로봇시스템학회 2010 제어로봇시스템학회 국제학술대회 논문집 Vol.2010 No.10
This paper presents a standoff distance control and a phase angle control for multiple aircraft to track a moving target. The roll angle command is generated to keep a constant distance from the target. The speed and the heading angle commands are generated to keep a constant phase angle between neighbor vehicles. Numerical simulation is performed to verify the tracking and collision performance of the proposed control laws.
Seungho Yoon,Youdan Kim,Sanghyuk Park 한국항공우주학회 2012 International Journal of Aeronautical and Space Sc Vol.13 No.1
An adaptive backstepping controller is designed for the automatic landing of a fixed-wing aircraft. The backstepping control scheme is adopted by using the nonlinear six degree-of-freedom dynamics of the aircraft during the landing phase. The adaptive law is integrated along with the backstepping controller in order to estimate the aircraft modeling errors as well as the external disturbance. The dynamic constraints of the states and the actuator inputs are taken into account in the parameter adaptation. This is done to prevent an aggressive adaptation and to provide reliable control commands. Numerical simulations were performed to verify the performance of the proposed control law for the landing of the aircraft with the presence of gust and actuator stuck.
무인항공기 자동착륙을 위한 나선형 강하궤적 및 종말유도 설계
윤승호(Seungho Yoon),김현진(H. Jin Kim),김유단(Youdan Kim) 한국항공우주학회 2010 韓國航空宇宙學會誌 Vol.38 No.3
본 논문에서는 고정익 무인항공기의 그물망 자동착륙을 위한 나선형 강하궤적과 종말 유도기법을 설계하였다. 시야가 확보된 좁은 지역에서 착륙하도록 고정익 항공기의 나선형 강하궤적을 설계하였고, 나선형 강하의 끝점에서 그물망 입사방향을 향하도록 비행경로각 명령을 생성하였다. 종말유도 단계에서는 그물망 중심으로의 정밀한 유도를 위하여 시선각 정보 기반 의사추적 유도기법을 설계하였다. 고정익 무인항공기의 시스템 인식 모델을 이용한 6자유도 수치 시뮬레이션을 수행하여 제안한 나선형 착륙비행의 성능을 검증하였다. This paper presents a spiral descending path and a landing guidance law for net-recovery of a fixed-wing unmanned aerial vehicle. The net-recovery landing flight is divided into two phases. In the first phase, a spiral descending path is designed from an arbitrary initial position to a final approaching waypoint toward the recovery net. The flight path angle is controlled to be aligned to the approaching direction at the end of the spiral descent. In the second phase, the aircraft is guided from the approaching waypoint to the recovery net using a pseudo pursuit landing guidance law. Six degree-of-freedom simulation is performed to verify the performance of the proposed landing guidance law.
이동 목표물 협력추적을 위한 다수 무인항공기의 분산형 확장정보필터 설계
윤승호(Seungho Yoon),배종희(Jonghee Bae),김유단(Youdan Kim) 한국항공우주학회 2011 韓國航空宇宙學會誌 Vol.39 No.11
본 논문에서는 이동 목표물을 추적하기 위하여, 다수 무인항공기의 측정치를 이용한 목표물의 위치와 속도 추정기법을 제안하였다. 항공기와 목표물 사이의 상대거리와 시선각 정보를 이용하여 목표물의 위치, 속도성분을 추정하는 확장필터를 구성하였다. 다수의 항공기 간 정보교환과 계산이 용이하도록 공분산 역행렬 형태의 정보필터를 설계하였다. 개별 확장필터, 부분 분산형 확장필터, 분산형 확장필터를 이용한 수치 시뮬레이션을 수행하여, 제안된 분산형 확장필터의 이동 목표물 추정 및 추적 성능을 검증하였다. This paper deals with the tracking problem of a moving target using multiple unmanned aerial vehicles. A decentralized extended information filter is designed to cooperatively estimate the position and the velocity of the moving target. The extended information filter is adopted to consider the range and the line-of-sight angle as measurement data. The decentralized scheme is applied to enhance the estimation performance using the information provided by other vehicles. Numerical simulation is performed to verify the tracking performance of the proposed decentralized filters.
윤승호(Seungho Yoon),배세린(Selin Bae),한용수(Youngsoo Han),김현진(Hyoun Jin Kim),김유단(Youdan Kim) 제어로봇시스템학회 2008 제어·로봇·시스템학회 논문지 Vol.14 No.12
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.