Fault Diagnosis of Attitude Control Thruster Based on the Extended State Observer

Author(s):  
Shuo Wang ◽  
Lihong Xiao ◽  
Huiping Zhang
2020 ◽  
Vol 10 (11) ◽  
pp. 3719
Author(s):  
Ran Jiao ◽  
Wusheng Chou ◽  
Yongfeng Rong ◽  
Mingjie Dong

Aerial operation with unmanned aerial vehicle (UAV) manipulator is a promising field for future applications. However, the quadrotor UAV manipulator usually suffers from several disturbances, such as external wind and model uncertainties, when conducting aerial tasks, which will seriously influence the stability of the whole system. In this paper, we address the problem of high-precision attitude control for quadrotor manipulator which is equipped with a 2-degree-of-freedom (DOF) robotic arm under disturbances. We propose a new sliding-mode extended state observer (SMESO) to estimate the lumped disturbance and build a backstepping attitude controller to attenuate its influence. First, we use the saturation function to replace discontinuous sign function of traditional SMESO to alleviate the estimation chattering problem. Second, by innovatively introducing super-twisting algorithm and fuzzy logic rules used for adaptively updating the observer switching gains, the fuzzy adaptive saturation super-twisting extended state observer (FASTESO) is constructed. Finally, in order to further reduce the impact of sensor noise, we invite a tracking differentiator (TD) incorporated into FASTESO. The proposed control approach is validated with effectiveness in several simulations and experiments in which we try to fly UAV under varied external disturbances.


2014 ◽  
Vol 721 ◽  
pp. 257-260
Author(s):  
Ping Liu ◽  
Wei Jie Sun

In this paper, a combing method based on the linear extended state observer (LESO) and the LQR controller is presented. The LESO is applied to estimate the total disturbance of the space station, and an effective disturbance compensation strategy is proposed for the attitude control and moment management. The simulation results illustrate this method is effective


2021 ◽  
Vol 0 (0) ◽  
Author(s):  
Yuteng Cao ◽  
Qi Liu ◽  
Guiqin He ◽  
Qiuling Zhao ◽  
Fang Liu

Abstract In this article, a three-axis attitude manoeuvre spacecraft consisting of a central rigid body and a rotating solar array is studied. The rotating solar array is considered a disturbance to the spacecraft. In the design of the controller, the coupled terms and the rotating solar array are considered a disturbance. The improved extended state observer is proposed by combing the sliding mode observer with the originally extended state observer to estimate the disturbance. The sliding mode control method is adopted to adjust the attitude of the spacecraft. Numerical simulations are presented to demonstrate the outstanding performance of the present observer.


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