• Title/Summary/Keyword: Flight controller

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A Study on Standardization on the Flight Controller Mode in Remotely Piloted Aircraft Drone : Focused on Drone Controller Mode Preference (원격조종항공기 드론 조종기모드 표준화 연구 : 드론 조종기모드 선호도를 중심으로)

  • Park, Wontae
    • Journal of the Society of Korea Industrial and Systems Engineering
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    • v.42 no.4
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    • pp.69-75
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    • 2019
  • Remotely Piloted Aircraft (RPA) controls as a type of unmanned aerial vehicle (drone) is growing rapidly and its flight controller stick disposition is required standardization. We should standardize RPA drone flight control disposition because the flight pilot of RPA is hard to be trained so the flight controller stick differences impairs safety and wastes time and effort of flight controller industry. So this study researches the on-going standardization of RPA drone flight control disposition in Korea and foreign countries. Also this paper analyzes and researches of expert about RPA drone flight controller function and application of flight control mode. I accomplished expert research about standardization plan of unmanned flight control mode and confirm the necessity. Nowadays mode1 and 2 are mostly used in Korea so I carried out preference investigation for two modes. There were 4 preferences choices of RPA drone control mode necessity (importance) and recommendation of standardization modes. They answered that necessity of standardization is important considering pilot training, flight safety and positive development of drone industry. The result of standardization mode preference is that they prefer mode 2 (drone maker 86%, training facilities and research facilities 58%, government bureau 60%). Overall preference result shows that mode 1 24%, mode 1&2 16%, mode 2 60%. So they preferred mode 2 by 60%. The differences between two modes are the direction of throttle and pitch. Direction of throttle and pitch operate opposite way. They prefer mode 2 because mode 2 has similarities of manned flight control mode. Significance of this study is that it showed the necessity of standardization and flight control preference in a quantitative way. It will help drone standardization in related industries and development direction near future.

Neural Networks Based Adaptive Flight Controller Design and Handling Quality Evaluation for Tiltrotor Aircraft (신경회로망을 이용한 틸트로터 항공기의 적응 비행제어기 설계 및 비행성 평가)

  • Lee, Ki Young;Kim, Byoung Soo
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.21 no.3
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    • pp.1-8
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    • 2013
  • An application of adaptive flight controller is required for the non-linear and high uncertain system that configuration of tiltrotor aircraft is dramatically changed from rotary wing mode to fixed wing mode. In this paper, the applicable adaptive controller for the tiltrotor aircraft was designed using Neural Networks and DMI (Dynamic Model Inversion). The performance of the SCAS (Stability and Control Augmentation System) was simulated against manned military specification, using the fullscale model of 'Smart UAV(Unmanned Aerial Vehicle)' developed by Korea Aerospace Research Institute. And Neural Networks based adaptive controller was verified through its whole operating envelope using the established HQ (Handling Quality) criteria.

Development of a Reconfigurable Flight Controller Using Neural Networks and PCH (신경회로망과 PCH을 이용한 재형상 비행제어기)

  • Kim, Nak-Wan;Kim, Eung-Tai;Lee, Jang-Ho
    • Journal of Institute of Control, Robotics and Systems
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    • v.13 no.5
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    • pp.422-428
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    • 2007
  • This paper presents a neural network based adaptive control approach to a reconfigurable flight control law that keeps handling qualities in the presence of faults or failures to the control surfaces of an aircraft. This approach removes the need for system identification for control reallocation after a failure and the need for an accurate aerodynamic database for flight control design, thereby reducing the cost and time required to develope a reconfigurable flight controller. Neural networks address the problem caused by uncertainties in modeling an aircraft and pseudo control hedging deals with the nonlinearity in actuators and the reconfiguration of a flight controller. The effect of the reconfigurable flight control law is illustrated in results of a nonlinear simulation of an unmanned aerial vehicle Durumi-II.

Design of Reconfigurable Flight Controller using Sliding Mode Control - Actuator Fault

  • dong ho Shin;Kim, Youdan
    • 제어로봇시스템학회:학술대회논문집
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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...

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Formation Geometry Center based Formation Controller Design using Lyapunov Stability Theorem

  • Lee, Ji-Eun;Kim, Hyeong-Seok;Kim, You-Dan;Han, KiHoon
    • International Journal of Aeronautical and Space Sciences
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    • v.9 no.2
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    • pp.71-78
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    • 2008
  • New formation flight controller for unmanned aerial vehicles is proposed. A behavioral decentralized control approach called formation geometry center control is adopted. Trajectory tracking as well as formation geometry keeping are the purpose of the formation flight, and therefore two controllers are designed: a trajectory tracking controller for reference trajectory tracking, and a position controller for formation geometry keeping. Each controller is designed using Lyapunov stability theorem to guarantee the asymptotic stability. Formation flight controller is finally obtained by combining the trajectory tracking controller and the formation geometry keeping controller using a weighting parameter that depends on the relative distance error between unmanned aerial vehicles. Numerical simulations are performed to validate the performance of the proposed controller.

Hovering Flight Control for a Model Helicopter using the Minimal-Order LQG/LTR Technique (Minimal Order LQG/LTR 기법에 의한 모형헬리콥터의 정지비행 자세제어)

  • Yang, J.S.;Han, K.H.;Lee, J.S.
    • Proceedings of the KIEE Conference
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    • pp.457-459
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    • 1998
  • This paper presents a 3-DOF hovering flight controller for a model helicopter using the minimal order LQG/LTR technique. A model helicopter is an unstable multi-input multi-output nonlinear system strongly exposed to disturbances, so a robust multi-variable control theory should be applied to control it. The minimal order LQG/LTR technique which uses a reduced-order observer in the LTR procedure is used to design the controller. Performances for the 3-DOF hovering flight controller are evaluated through computer simulations.

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Design of hovering flight controller for a model helicopter

  • Shim, Hyeoncheol;Lee, Ho-Eun;Park, Hyunsik;Lee, Kyo-Il
    • 제어로봇시스템학회:학술대회논문집
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    • pp.344-348
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    • 1992
  • This paper describes a procedure to design a hovering flight controller for a model helicopter using LQG theory. Parameters of the model helicopter in hover are obtained using direct measurements and calculations proposed by other research. A feedback co is by using digital LQG theory. First, a full state feedback controller is designed to the discretized system taking desirable transient response and other assumptions into account. Then a full-state estimator is designed and revised until desirable response is obtained while global stability is maintained. Performance of the controller is tested by computer simulations. Experiments have been performed using a 3-degree-of-freedom gimbal that holds the model helicopter, and the controller exhibited stable hover capability.

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Analysis on Flight Test Results of Reconfiguration Flight Control System (재형상 비행제어 시스템의 비행시험 결과 분석)

  • Min, Byoung-Mun;Kim, Seong-Pil;Kim, Bong-Ju;Kim, Eung-Tai;Tahk, Min-Jea
    • Journal of Institute of Control, Robotics and Systems
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    • v.14 no.12
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    • pp.1244-1252
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    • 2008
  • This paper presents the analysis results obtained by the flight test of reconfiguration flight control system for an aircraft. The reconfiguration flight control system was designed by using control allocation scheme that automatically distributes the demanded control moments determined by control law to each actual control surface. In this paper, some control allocation algorithms for reconfiguration control of general aircraft with redundant control surfaces are summarized and their performance evaluation results through nonlinear simulation and Hardware-In-the-Loop-Simulation (HILS) test are shown. Also, Unmanned Aerial Vehicle (UAV) system adopted as a platform for the flight test of reconfiguration flight controller and the implementation procedure of reconfiguration flight controller into real-time UAV system were introduced. Finally, flight test results were analyzed.

Balance Control of Drone using Adaptive Two-Track Control (적응적 Two-Track 기술을 이용한 드론의 균형 제어)

  • Kim, Jang-Won
    • The Journal of Korea Institute of Information, Electronics, and Communication Technology
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    • v.12 no.6
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    • pp.666-671
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    • 2019
  • The flight controller(FC) used in small-sized drone was developed as simple structure does not perform complex operations because it uses different MCU with large-sized drone. Also, the balance control of small-sized drone should be simpler than Kalman filter using complex filter and the method using Complementary filter has relatively more operations. So, the method to realize the balance control on small-sized drone effectively using two-track control operating as proper method for above is suggested in this research. This method is a system maintaining effective balance with simple structure and less operations by operating adaptively for the unbalance of the drone with the acceleration sensor with the advantage which performing accurate correction by data processing for long term change and gyroscope sensor maintaining the balance of the drone by data processing for short term change. It is confirmed that stable operation was performed mostly based on the test result for repeatable test more than 100 times using two-track control and it maintained normal state operation more than 98% excluding the difficulty of maintaining normal operation when meets sudden and rapid wind yet.

Flight control of a small unmanned aerial vehicle using a dynamic compensator (동적 보상기를 이용한 소형 무인항공기 비행 제어)

  • Kim, Heui-Joo;Kim, Jea-Wook;Lee, Kang-Woong
    • Journal of Advanced Navigation Technology
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    • v.16 no.4
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    • pp.571-577
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    • 2012
  • In this paper, we design a flight controller using a dynamic compensator for a small unmanned aerial vehicle. The proposed method ensures flight stability during altitude holding and waypoints passing by improving the transient response and steady state error. The control system consists of dual feedback loops with an inner loop and a outer loop. The inner loop has a PD controller to improves the transient response and the outer loop has a dynamic compensator to reduce overshoot in the transient response and improve the steady state error. The performance of the proposed method is evaluated by flight test on a small UAV.