• 제목/요약/키워드: Auto-Landing

검색결과 19건 처리시간 0.034초

Design of A Simulation S/W for Evaluation of Auto-Landing Algorithms

  • Yoon sug-joon;Kim kang-soo;Ahn jae-joon
    • 한국시뮬레이션학회:학술대회논문집
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    • 한국시뮬레이션학회 2003년도 춘계학술대회논문집
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    • pp.3-8
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    • 2003
  • A Simulation S/W is developed to evaluate performances of MLS (Microwave Landing System) and IBLS(Integrated Beacon Landing System) in precision auto-landing. For this study classical PID and optimal LQG controllers are developed as well as mathematical models of MLS and IBLS. Ship-landing condition is also considered by assuming sinusoidal movement of the ship in the pitch direction. The simulated aircraft is F-16 in the study of precision auto-landing. For the integrated simulation environment GUI windows are designed for input of parameter values necessary for simulation, such as vehicle performance and environmental data. For validation and verification of models various comparison graphs of simulation outputs are comprised in the GUI design as well as 3D visual simulation of vehicle dynamics.

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Auto-Landing Guidance System Design for Smart UAV

  • Min, Byoung-Mun;Shin, Hyo-Sang;Tahk, Min-Jea;Kim, Boo-Min;Kim, Byoung-Soo
    • 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.

A Study on the Longitudinal and Lateral Errors of Air Vehicle Heading for Auto-landing

  • Park, Ji Hee;Park, Hong Sick;Shin, Chul Su;Jo, Young-Wo;Shin, Dong-Ho
    • Journal of Positioning, Navigation, and Timing
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    • 제2권2호
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    • pp.115-121
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    • 2013
  • For the auto-landing operation of an air vehicle, the possibility of auto-landing operation should be first evaluated by testing the navigation performance through a flight test. In general, navigation performance is tested by analyzing north/east/down (NED) errors relative to reference equipment whose precision is about 8~10 times higher than that of a navigation system. However, to evaluate the auto-landing operation of an air vehicle, whether the air vehicle approaches a glide path aligned with the runway, within a specific error, needs to be examined rather than examining the north/east errors of the navigation system. Therefore, the longitudinal/lateral errors of air vehicle heading need to be analyzed. In this study, a method for analyzing the longitudinal/lateral errors of a navigation system was proposed as the navigation performance test method for evaluating the safety during the auto-landing of an air vehicle. Also, flight tests were performed six times, and the safety of auto-landing was examined by analyzing the performance using the proposed method.

Automatic Landing in Adaptive Gain Scheduled PID Control Law

  • Ha, Cheol-Keun;Ahn, Sang-Won
    • 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.

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무인기용 착륙장치 측력 모델링 및 지상활주 제어기 설계 (Side Force Modeling of Landing Gear and Ground Directional Controller Design for UAV)

  • 조성봉;안종민;허기봉
    • 한국항공우주학회지
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    • 제42권12호
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    • pp.997-1003
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    • 2014
  • 무인항공기의 자동이착륙을 성공적으로 수행하기 위해서는 자동 지상활주 제어는 반드시 설계되어야 하는 중요한 부분이다. 이러한 지상활주 제어기를 설계하기 위해서는 정확하고 신뢰도 높은 착륙장치 모델은 반드시 필요하다. 본 연구에서는 착륙장치 모델링을 완성하기 위해서 특별히 착륙장치 측력 모델링을 수행하였다. 조향각 명령을 포함한 Cornering Angle을 계산하여 측력을 모델링하였다. 그리고 모델링된 착륙장치 모델을 포함한 비선형 6자유도 시뮬레이션 환경을 이용하여, 항공기의 바람벡터 방향인 Course Angle 오차를 해소하기 위한 전륜 조향(Nose Wheel Steering)과 러더 조향(Rudder Steering)을 동시에 이용하는 자동 지상활주 제어기를 설계하였다. 설계된 지상활주 제어기를 동일하게 적용하여, 착륙장치 모델을 포함한 시뮬레이션 결과와 실제 무인기를 이용한 자동 지상활주 시험 결과를 비교하였고, 이로써 착륙장치 측력 모델링과 지상활주 제어기의 정확성을 입증하였다.

Design of Longitudinal Auto-landing Guidance and Control System Using Linear Controller-based Adaptive Neural Network

  • Choi, Si-Young;Ha, Cheol-Keun
    • 제어로봇시스템학회:학술대회논문집
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    • 제어로봇시스템학회 2005년도 ICCAS
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    • pp.1624-1627
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    • 2005
  • We proposed a design technique for auto-landing guidance and control system. This technique utilizes linear controller and neural network. Main features of this technique is to use conventional linear controller and compensate for the error coming from the model uncertainties and/or reference model mismatch. In this study, the multi-perceptron neural network with single hidden layer is adopted to compensate for the errors. Glide-slope capture logic for auto-landing guidance and control system is designed in this technique. From the simulation results, it is observed that the responses of velocity and pitch angle to commands are fairly good, which are directly related to control inputs of throttle and elevator, respectively.

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RTK를 이용한 회전익 드론 정밀 착륙 실험 (Experiments of RTK based Precision Landing for Rotary Wing Drone)

  • 김영규;장진웅;이종휘;유종호;백승현;김대년
    • 대한임베디드공학회논문지
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    • 제18권2호
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    • pp.75-80
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    • 2023
  • Unmanned drone stations for automatic charging have been developed in order to overcome the flying time limitation of rotary wing drones. Since the drone stations is an unmanned operating system, each of the drones will be required to have a high degree of landing accuracy. Drone precision landing has been mainly studied depended on image processing technologies, but the image processing systems make several problems, such as the mission weight, the drone cost, and the development complexity increases, and the flight time decrease. Thus, this paper researched accuracy of precision landing based on RTK (real time kinetics) for rotary wing drones. For the experiments of RTK based precision landing, a drone repeatedly performed three missions. The survey accuracies of the RTK about missions respectively were set as 0.3, 0.2, and 0.1 meters. Each mission has one take-off point, two way-points and one landing-point, and was repeated ten times. The experiment results revealed landing error distance means of around 0.258, 0.12 and 0.057 meters on each of RTK setting.

Shell Landing 최적화 시스템 개발 (Development of Optimization System in Shell Landing)

  • 임형균;김재철;이지현;신준식
    • 대한조선학회 특별논문집
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    • 대한조선학회 2011년도 특별논문집
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    • pp.90-94
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    • 2011
  • Longitudinal shell member that arranged block unit on 3D-curved surface is performed manual working by designer considering spacing of division characteristic, location and twisting at geometrical 3-dimensional form. Shell expansion drawing that drawn by initial design and shell landing work performed by hull production design have overlap of design work in terms of arrangement of shell longitudinal member. In this study, eliminate design overlap on shell member arrangement that is one of ship longitudinal member. Develop shell member optimization and auto arrangement system.

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Real-Time Container Shape and Range Recognition for Implementation of Container Auto-Landing System

  • Wei, Li;Lee, Eung-Joo
    • 한국멀티미디어학회논문지
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    • 제12권6호
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    • pp.794-803
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    • 2009
  • In this paper, we will present a container auto-landing system, the system use the stereo camera to measure the container depth information. And the container region can be detected by using its hough line feature. In the line feature detection algorithm, we will detect the parallel lines and perpendicular lines which compose the rectangle region. Among all the candidate regions, we can select the region with the same aspect-ratio to the container. The region will be the detected container region. After having the object on both left and right images, we can estimate the distance from camera to object and container dimension. Then all the detect dimension information and depth inform will be applied to reconstruct the virtual environment of crane which will be introduce in this paper. Through the simulation result, we can know that, the container detection rate achieve to 97% with simple background. And the estimation algorithm can get a more accuracy result with a far distance than the near distance.

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경사지에서 운용 가능한 대형 차량형 플랫폼 장비 자동수평조절장치의 동적 거동 (Dynamic Behavior Analysis of the Auto-leveling System for Large Scale Transporter Type Platform Equipment on the Ground Slope)

  • 하태완;박정수
    • 한국군사과학기술학회지
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    • 제23권5호
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    • pp.502-515
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    • 2020
  • To identify the dynamic characteristics of the Auto-leveling system applied to the Tractor-Trailer type Transporter for mounting a large scale precision equipment, Dynamics Modeling & Simulation were performed using general Dynamics Analysis Program - RecurDyn(V9R2). The axial load data, transverse load data and pad trace data of leveling actuators were obtained from M&S. And they were analyzed and compared with each other by parameters, i.e. friction coefficients on the ground, landing ram speed of actuators, and direction & quantity of ground slope. It was observed that ground contact friction coefficients affected to transverse load and pad trace; the landing ram speed of actuators to both amplitude of axial & transverse load, and this phenomena was able to explain from the frequency analysis of the axial load data; the direction of ground slope to driving sequence of landing ram of actuators. But the dynamic behaviors on the two-directional slope were very different from them on the one-directional slope and more complex.