Tuning of Active Disturbance Rejection Attitude Controller for Statically Unstable Launch Vehicle

2017 ◽  
Vol 54 (6) ◽  
pp. 1383-1389 ◽  
Author(s):  
Qixia Wu ◽  
Mingwei Sun ◽  
Zengqiang Chen ◽  
Zhihong Yang ◽  
Zenghui Wang
Keyword(s):  
Disturbance Rejection ◽  
Launch Vehicle ◽  
Active Disturbance Rejection ◽  
Attitude Controller

Research on Attitude Control of Spacecraft Based on ADRC

2011 ◽  
Vol 383-390 ◽  
pp. 358-365 ◽  
Author(s):  
Fu Lin Teng ◽  
Hong Yu Ge ◽  
Hong Sheng Li ◽  
Jian Hua Zhang
Keyword(s):  
Attitude Control ◽  
Disturbance Rejection ◽  
High Performance ◽  
Control Technology ◽  
Attitude Control System ◽  
Active Disturbance Rejection ◽  
Disturbance Rejection Control ◽  
Simulation And Experiment ◽  
Attitude Controller ◽  
Very High

Modern spacecraft demands from an attitude control system very high performance and accuracy, and many new features, such as disturbance rejection capability. The recently developed active disturbance rejection control technology is applied to the attitude control of spacecraft subject to disturbances and parametric uncertainties. Simulation and experiment show significant advantages of the proposed attitude controller over the controller resulting from conventional PID approach.

scholarly journals A Novel Linear Active Disturbance Rejection Control Design for Air-Breathing Supersonic Vehicle Attitude System with Prescribed Performance

2020 ◽  
Vol 2020 ◽  
pp. 1-15
Author(s):  
Chao Ming ◽  
Xiaoming Wang
Keyword(s):  
Disturbance Rejection ◽  
Tracking Error ◽  
Transient State ◽  
Control Technique ◽  
Active Disturbance Rejection Control ◽  
Air Breathing ◽  
Prescribed Performance ◽  
Active Disturbance Rejection ◽  
Disturbance Rejection Control ◽  
Attitude Controller

This paper investigates the design problem of the attitude controller for air-breathing supersonic vehicle subject to uncertainties and disturbances. Firstly, the longitudinal model is established for the attitude controller design which is devised as a strict feedback formulation, and a transformed tracking error is derived with the prescribed performance control technique such that it can limit the tracking error to a predefined region. Then, a novel linear active disturbance rejection control scheme is proposed for the attitude system to enhance the steady-state and transient-state performances by incorporating the transformed tracking error. On the basis of the Lyapunov stability theorem, the convergence and stability characteristics are both rigorously proved for the closed-loop system. Finally, extensive contrast simulations are conducted to demonstrate the effectiveness, robustness, and advantage of the proposed control strategy.

Manipulation strategy of tilt quad rotor based on active disturbance rejection control

2019 ◽  
Vol 234 (3) ◽  
pp. 573-584 ◽  
Author(s):  
Zhigang Wang ◽  
Jianbo Li ◽  
Dengyan Duan
Keyword(s):  
Sliding Mode Control ◽  
Disturbance Rejection ◽  
Sliding Mode ◽  
Active Disturbance Rejection Control ◽  
Transition Mode ◽  
Mode Control ◽  
Active Disturbance Rejection ◽  
Disturbance Rejection Control ◽  
Attitude Controller ◽  
Manipulation Strategy

To solve the problem of manipulation redundancy and coupling in transition mode of tilt quad rotor, this paper studied the manipulation strategy in transition mode, and carried out the design of the attitude controller based on active disturbance rejection control (ADRC) with sliding mode control in nonlinear state error feedback (NLSEF). According to the characteristics of flight in transition mode, the rudders and propellers were assigned different control rights. The differential output of the tracking differentiator was used as the attitude angular rate instruction to simplify the structure of the attitude controller. Extended state observer was used to estimate and compensate internal and external uncertainties. The sliding mode control in NLSEF was used to improve response speed of the controller. Through the flight control simulation and flight test of the tilt quad rotor, the validity of the control system and the rationality of the manipulation strategy were verified.

Active disturbance rejection attitude control of unmanned quadrotor via paired coevolution pigeon-inspired optimization

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Yang Yuan ◽  
Haibin Duan
Keyword(s):  
Attitude Control ◽  
Disturbance Rejection ◽  
Sliding Mode ◽  
Parameters Identification ◽  
Control Law ◽  
Terminal Sliding Mode ◽  
External Interference ◽  
Content Type ◽  
Active Disturbance Rejection ◽  
Attitude Controller

Purpose The purpose of this paper is to develop a novel active disturbance rejection attitude controller for quadrotors and propose a controller parameters identification approach to obtain better control results. Design/methodology/approach Aiming at the problem that quadrotor is susceptible to disturbance in outdoor flight, the improved active disturbance rejection control (IADRC) is applied to design attitude controller. To overcome the difficulty that adjusting the parameters of IADRC controller manually is complex, paired coevolution pigeon-inspired optimization (PCPIO) algorithm is used to optimize the control parameters. Findings The IADRC, where nonlinear state error feedback control law is replaced by non-singular fast terminal sliding mode control law and a third-order tracking differentiator is designed for second derivative of the state, has higher control accuracy and better robustness than ADRC. The improved PIO algorithm based on evolutionary mechanism, named PCPIO, is proposed. The optimal parameters of ADRC controller are found by PCPIO with the optimization criterion of integral of time-weighted absolute value of the error. The effectiveness of the proposed method is verified by a series of simulation experiments. Practical implications IADRC can improve the accuracy of attitude control of quadrotor and resist external interference more effectively. The proposed PCPIO algorithm can be easily applied to practice and can help the design of the quadrotor control system. Originality/value An improved active disturbance rejection controller is designed for quadrotor attitude control, and a hybrid model of PIO and evolution mechanism is proposed for parameters identification of the controller.

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