• 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.

• 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.

• ETRI Journal
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• 제45권5호
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• pp.746-757
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• 2023

This study presents a novel safe landing algorithm for urban drone deliveries. The rapid advancement of drone technology has given rise to various delivery services for everyday necessities and emergency relief efforts. However, the reliability of drone delivery technology is still insufficient for application in urban environments. The proposed approach uses the "landing angle control" method to allow the drone to land vertically and a rapidly exploring random tree-based collision avoidance algorithm to generate safe and efficient vertical landing paths for drones while avoiding common urban obstacles like trees, street lights, utility poles, and wires; these methods allow for precise and reliable urban drone delivery. We verified the approach within a Gazebo simulation operated through ROS using a six-degree-of-freedom drone model and sensors with similar specifications to actual models. The performance of the algorithms was tested in various scenarios by comparing it with that of stateof-the-art 3D path planning algorithms.

• 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.1103-1111
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• 2014

The results of control law design for a tilt-rotor unmanned aerial vehicle that has a nacelle mounted wing extension (WE) are presented in this paper. It consists of a control surface mixer, stability and control augmentation system (SCAS), hold mode for altitude / speed / heading, and a guidance mode for preprogram and point navigation which includes automatic take-off and landing. The conversion corridor and the control moments derivatives between the original tilt-rotor and its variant of the nacelle mounted WE were compared to show the effectiveness of the WE. The nacelle conversion of the original tilt-rotor starts when the airspeed is greater than 30 km/h but its WE variant starts at 0 km/h in order to reduce the drag caused by the high incidence angle of the WE. The stability margins of the inner loop are presented with the optimization approach. The outer loops for the hold mode are designed with trial and error methods with linear and nonlinear simulation. The main control parameter for altitude control of the helicopter mode is thrust command and it is transferred to the pitch attitude command in airplane mode. Otherwise, the control parameter for the speed of the helicopter mode is the pitch attitude command and it is transferred to the thrust command in airplane mode. Therefore the speed and altitude hold mode are coupled to each other and are engaged at the same time when an internal pilot engages any of the altitude or speed hold modes. The nonlinear simulation results of the guidance control for the preprogrammed mode and point navigation are also presented including automatic take-off and landing in order to prove the full control law.

• 한국항공우주학회지
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• 제38권3호
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• pp.228-235
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• 2010

본 논문에서는 틸트로터 항공기의 회전익 모드에 대한 자율비행 유도제어 알고리즘을 적응제어기법을 이용하여 설계하는 것이다. 이를 위해 우선 출력기반 근사적 궤환선형화 기법을 통하여 알고리즘의 내부루프를 구성하고 그로부터 발생하는 모델오차를 단일 은닉층-신경망을 적용하여 상쇄하였다. 그리고 리아푸노프 안정성 이론에 따른 적응제어 갱신법칙은 선형 관측기를 기반으로 설계하였다. 나아가 외부루프는 경로점 유도법칙으로부터 생성되는 궤적을 추종하도록 하였으며 특히 엄밀한 자동착륙 궤적추종 성능 향상을 위하여 방향각 및 비행경로각 시선유도법칙을 설계하였다. 틸트로터 비선형 모델 시뮬레이션 결과는 콜렉티브 입력에서 보이는 순간적인 작동기 포화현상 이외에는 만족할 만한 안정성과 추종성능을 보여 주고 있다.

• 한국항행학회논문지
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• 제28권3호
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• pp.254-261
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• 2024

항공기 이착륙 시 정확한 유도는 중요하며, 이를 위해 계기착륙시스템 ILS (instrument landing system) 가 이용된다. 안정된 ILS 운용을 위하여 정기 점검이 진행되며, 지상차량 및 측정항공기 외 드론을 이용한 점검 수행 연구가 있다. 광대역 주파수 수신용 SDR과 단일보드컴퓨터를 이용하고, GNU Radio를 통해 ILS의 로컬라이저 신호를 수신 처리하는 소형시스템을 설계하였다. GNU Radio를 통한 신호처리 특성을 실행하고 MATLAB Simulink로 시뮬레이션 및 이론 값을 확인하는 과정을 거쳤다. 이를 통해 항공기가 활주로 진입할 때 DDM (difference in depth of modulation)과 진입 각도를 계산할 수 있다. 또한 GNU Radio에서 TCP (transmission control protocol)를 통해 무선으로 실시간 신호를 처리할 수 있게 구현하였다. 이를 활용해 항공기가 활주로 중심선으로 진입할 때는 약 0.5%, 1도 각도로 진입할 때는 0.27% 이내 오차가 있는 결과를 얻었다. 항공기 또는 지상 차량 이용 ILS 신호 검사 및 유지보수 방식과 비교하여 차별성이 있는 드론 이용 검사에 장착 가능한 소형 SDR 사용 수신시스템 구현을 가능하게 할 것이라 예상한다.