scholarly journals A Blended Sliding Mode Control with Linear Quadratic Integral Control based on Reduced Order Model for a VTOL System

Author(s):  
Marco Herrera ◽  
Paulo Leica ◽  
Danilo Chávez ◽  
Oscar Camacho
2020 ◽  
Vol 53 (2) ◽  
pp. 6207-6212
Author(s):  
Kiran Kumari ◽  
Bijnan Bandyopadhyay ◽  
Johann Reger ◽  
Abhisek K. Behera

2018 ◽  
Vol 2018 ◽  
pp. 1-22 ◽  
Author(s):  
Rongrong Yang ◽  
Yongling Fu ◽  
Ling Zhang ◽  
Haitao Qi ◽  
Xu Han ◽  
...  

A novel sliding mode control (SMC) design framework is devoted to providing a favorable SMC design solution for the position tracking control of electrohydrostatic actuation system (EHSAS). This framework is composed of three submodules as follows: a reduced-order model of EHSAS, a disturbance sliding mode observer (DSMO), and a new adaptive reaching law (NARL). First, a reduced-order model is obtained by analyzing the flow rate continuation equation of EHSAS to avoid the use of a state observer. Second, DSMO is proposed to estimate and compensate mismatched disturbances existing in the reduced-order model. In addition, a NARL is developed to tackle the inherent chattering problem of SMC. Extensive simulations are conducted compared with the wide adoption of three-loop PID method on the cosimulation platform of EHSAS, which is built by combining AMESim with MATLAB/Simulink, to verify the feasibility and superiority of the proposed scheme. Results demonstrate that the chattering can be effectively attenuated, and the mismatched disturbance can be satisfyingly compensated. Moreover, the transient performance, steady-state accuracy, and robustness of position control are all improved.


2007 ◽  
Vol 4 (4) ◽  
pp. 329-334 ◽  
Author(s):  
B. Bandyopadhyay ◽  
Alemayehu G/Egziabher Abera ◽  
S. Janardhanan ◽  
Victor Sreeram

2016 ◽  
Vol 28 (6) ◽  
pp. 936-948 ◽  
Author(s):  
Yi Yang ◽  
◽  
Wei Wang ◽  
Daisuke Iwakura ◽  
Akio Namiki ◽  
...  

[abstFig src='/00280006/18.jpg' width='300' text='Hovering with 5 rotors' ] This study presents a fault-tolerance approach for hexacopters with failed propulsion systems (i.e., motors and propellers) using sliding mode control theory. In this study, we use an explicit control allocation method with linear constraints for allocating the control input to redundancy actuators, as well as a new sliding model controller designed to stabilize the attitude and maintain the basic flight performance of a vehicle with a single failed motor during an outdoor autonomous flight mission. An asymmetrical motor rotation arrangement is applied in order to ensure controllability for all degrees of freedom. We verify the developed system on a real hexacopter suffering propulsion-system failure. Finally, the comparative results between the linear-quadratic-integral controller and model reference sliding mode controller are presented to evaluate the robustness of each controller against the failure of redundancy actuators.


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