Mode Control
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2021 ◽  
Vol 96 ◽  
pp. 107491
Author(s):  
Chang Liu ◽  
Shaoshan Sun ◽  
Chenggang Tao ◽  
Yingxin Shou ◽  
Bin Xu

2021 ◽  
Vol 96 ◽  
pp. 107505
Author(s):  
Xia Wang ◽  
Shaoshan Sun ◽  
Chenggang Tao ◽  
Bin Xu

2021 ◽  
Vol 96 ◽  
pp. 107506
Author(s):  
Guangchen Zhang ◽  
Xufei Li ◽  
Yuanqing Xia

2021 ◽  
Vol 240 ◽  
pp. 109881
Author(s):  
Zhenchun Wang ◽  
Feng Luan ◽  
Nianguo Wang

2021 ◽  
Vol 96 ◽  
pp. 107497
Author(s):  
Guowei Xu ◽  
Shaoda Zhao ◽  
Yi Cheng

Author(s):  
Ji Eun Lee ◽  
Seok Kwon Jeong

Author(s):  
Majeed Mohamed ◽  
Madhavan Gopakumar

The evolution of large transport aircraft is characterized by longer fuselages and larger wingspans, while efforts to decrease the structural weight reduce the structural stiffness. Both effects lead to more flexible aircraft structures with significant aeroelastic coupling between flight mechanics and structural dynamics, especially at high speed, high altitude cruise. The lesser frequency separation between rigid body and flexible modes of flexible aircraft results in a stronger interaction between the flight control system and its structural modes, with higher flexibility effects on aircraft dynamics. Therefore, the design of a flight control law based on the assumption that the aircraft dynamics are rigid is no longer valid for the flexible aircraft. This paper focuses on the design of a flight control system for flexible aircraft described in terms of a rigid body mode and four flexible body modes and whose parameters are assumed to be varying. In this paper, a conditional integral based sliding mode control (SMC) is used for robust tracking control of the pitch angle of the flexible aircraft. The performance of the proposed nonlinear flight control system has been shown through the numerical simulations of the flexible aircraft. Good transient and steady-state performance of a control system are also ensured without suffering from the drawback of control chattering in SMC.


Author(s):  
Amit Kumar ◽  
◽  
Pradeep Kumar ◽  

This paper expresses about comparative power quality analysis in between conventional and proposed control techniques of DSTATCOM under different loading conditions. The goal of DSTATCOM is to reduce power quality problems, that occur due to an unbalanced load, non-linear load, power electronics based load and polluted grid. The performances of DSTATCOM are different in the different control techniques. Three conventional and one proposed control techniques have been employed in the DSTATCOM. Synchronous reference frame (SRF), Sliding mode control (SMC) and ADALINE based LMS control are the conventional techniques while enhanced SRF SOGI-FLL is the proposed technique. The control techniques of DSTATCOM have been compared in terms of load balancing, power factor enhancement, DC link voltage regulation and minimization of harmonics. These control techniques extract reference current for the PWM which generates switching pulses for the DSTATCOM. The complete H-bridge DSTATCOM system along with these control techniques have been implemented in MATLAB /Simulink platform and after execution, superior power quality features of proposed control technique has been investigated.


Author(s):  
Jiehua Feng ◽  
Dongya Zhao ◽  
Xing-Gang Yan ◽  
Sarah K Spurgeon

In this paper, a class of uncertain linear systems with unmatched disturbances is considered, where the nominal system representation is allowed to be non-minimum phase. A sliding surface is designed which is dependent on the system output, observed state, and estimated uncertain parameters. A linear coordinate transformation is introduced so that the stability analysis of the reduced-order sliding mode dynamics can be conveniently performed. A robust output feedback sliding mode control (OFSMC) is then designed to drive the considered system state to reach the sliding surface in finite time and maintain a sliding motion thereafter. A simulation example for a high incidence research model (HIRM) aircraft is used to demonstrate the effectiveness of the proposed method.


Energies ◽  
2021 ◽  
Vol 14 (20) ◽  
pp. 6532
Author(s):  
Wenlong Feng ◽  
Xiangyin Zhang

A neural network-based global fast terminal sliding mode control method with non-linear differentiator (NNFTSMC) is proposed in this paper to design the dynamic control system for three-axis stabilized platform. The dynamic model of the three-axis stabilized platform is established with various uncertainties and unknown external disturbances. To overcome the external disturbance and reduce the output chatter of the classical sliding mode control (SMC) system, the improved global fast terminal sliding mode control method using the nonlinear differentiator and neural network techniques is proposed and implemented in the three-axis stabilized platform system. The global fast terminal sliding mode controller can make the controlled state approach to the sliding surface in a finite time. To eliminate the system output chatter, the nonlinear differentiator is employed to obtain the differentiation of the signal. The neural network is introduced to estimate the uncertainties disturbances to improve the stability and the robustness of the control system. The stability and the robustness of the proposed control method are analyzed using the Lyapunov theory. The performance of the proposed NNFTSMC method is verified and compared with the classical proportion-integral-differential (PID) controller, SMC controller and fast terminal sliding mode controller (FTSMC) through the computer simulation. Results validate the effectiveness and robustness of the proposed NNFTSMC method in presence of uncertainties and unknown external disturbances.


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