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Trajectory tracking of tail-sitter aircraft by L_(1)adaptive fault tolerant control

Journal of Systems Engineering and Electronics 2021年第6期32卷 1477-1489页

作者： LI Zhaoying SHI Shuai LIU Hao School of Astronautics Beihang UniversityBeijing 100191China

This paper proposes an L_(1)adaptive fault tolerant control method for trajectory tracking of tail-sitter aircraft in the state of motor loss *** tail-sitter model considers the uncertainties produced by the features of nonlinearities and couplings which cause difficulties in *** L_(1)adaptive controller is designed to reduce the position and attitude error when actuators have faults.A reference trajectory containing large maneuver flight transitions is designed,which makes it even harder for the L_(1)controller to track *** are designed to assist L_(1)adaptive controller tracking of the reference *** stability of the L_(1)adaptive controller including compensators is ***,the simulation results are used to analyse the effectiveness of the proposed *** to the H∞controller,the L_(1)adaptive controller with compensators has better performance in position control and attitude control under fault tolerance state even when the aircraft conducts large ***,as the L_(1)adaptive control method separates feedback control and adaptive law design,the response speed of the whole system is improved.

关键词： tail-sitter aircraft fault tolerance trajectory tracking L_(1)adaptive controller

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Robust attitude control for a tail-sitter aircraft 36

Robust attitude control for a tail-sitter aircraft

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第36届中国控制会议

作者： Lixin Zhang Zhaoying Li Hao Liu Chao Wang School of Astronautics Beihang University

ISBN: (纸本)9781538629185

Many challenges of modeling and control exist in the tail-sitter aircraft,including parameter uncertainty,highly coupling,nonlinearity,and external *** this paper,the model of a tail-sitter aircraft is simplified at the nominal condition to obtain the nominal linear invariant *** a robust controller based on the H control theory is proposed to deal with the attitude tracking control problem and decrease the effects of multiple *** is proved that the closed-loop system has robust stability,and the tracking error can converge to *** is shown that the proposed robust controller can maintain the attitude angle adjustment accuracy and robustness to the model uncertainty and external disturbance.

关键词： tail-sitter aircraft attitude dynamics robust control

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Modeling and Active Disturbance Rejection Controller Design for Longitudinal Attitude of a tail-sitter aircraft

Modeling and Active Disturbance Rejection Controller Design ...

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第40届中国控制会议

作者： Jiajia Hou Xinglu Xia Ding Yang Ying Wang Zhichao Jiang Jianlin Feng Science and Technology on Space Physics Laboratory Beihang University

The active disturbance rejection control scheme is one of the most popular approaches to nonlinear systems and it is known that active disturbance rejection controllers have a better performance than the traditional PID controllers. This paper focuses on the active disturbance rejection controller design of a tail-sitter aircraft which can take off and land vertically as multi-rotor unmanned aerial vehicles and can cruise like fixed-wing unmanned aerial vehicles. A traditional PID controller is also designed to be compared with the active disturbance rejection controller. Numerical simulations are conducted and the fastness and anti-jamming of the active disturbance rejection controller are validated by the results.

关键词： Active Disturbance Rejection Control tail-sitter aircraft PID Controller

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A bio-inspired flight control strategy for a tail-sitter unmanned aerial vehicle

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Science China(Information Sciences) 2020年第7期63卷 88-97页

作者： Bin ZHU Jianzhong ZHU Qingwei CHEN Institute of Automation Nanjing University of Science and Technology Department of Energy and Power Engineering Tsinghua University

Wingbeat behavior and intermittent flight path are the two main characteristics of many *** this paper, to improve the efficiency of energy use and cruise range, a bio-inspired intermittent flight strategy with a whole flight envelope has applied to a tail-sitter aircraft. A total energy control system based transition control law has been proposed. The energy efficiency is investigated in terms of energy consumption per unit distance of different cruising modes, and the effectiveness and stability of proposed flight mode transition control law are verified by simulation. The mean mechanical power in flap-gliding flight is reduced compared with steady flight.

关键词： tail-sitter aircraft climb-glide total energy control system energy consumption minimization flight path

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