Imagen de Portada

Research on Hybrid Control Methods for Electromechanical Actuation Systems Under the Influence of Nonlinear Factors

Guardado en:
Publicado en:Actuators vol. 14, no. 11 (2025), p. 526-557
Autor principal: Ding Xingye
Otros Autores: Zhou, Yong
Publicado:
MDPI AG
Materias:
Amplitudes
Actuation
Accuracy
Proportional integral derivative
Mathematical models
Aviation
Control systems
Control stability
Systems stability
Control surfaces
Computer simulation
Friction
Aircraft
Simulation
Velocity
Control theory
Control algorithms
Coordinate transformations
Neural networks
Radial basis function
Numerical analysis
Controllers
Design
Sliding mode control
Integrated approach
Nonlinear control
Hybrid control
Control methods
Digitization
Step response
Acceso en línea:Citation/Abstract
Full Text + Graphics
Full Text - PDF
Etiquetas: Agregar Etiqueta
Sin Etiquetas, Sea el primero en etiquetar este registro!
Resumen:With the comprehensive digitalization and electrification of aircraft, electromechanical actuation systems (EAS) have been increasingly applied. However, EAS are affected by various nonlinear factors, such as friction and mechanical backlash, which can compromise system stability and control accuracy, thereby reducing the operational lifespan of the EAS. This study focuses on these two nonlinear factors and proposes a hybrid control approach to mitigate their effects. In the speed loop of the EAS, a Super-Twisting sliding mode controller combined with a generalized proportional–integral observer (GPIO) is designed, while in the position loop, a hybrid controller integrating a radial basis function (RBF) neural network with sliding mode control is implemented. Leveraging the advantages of numerical analysis in SIMULINK and dynamic simulation in ADAMS, a co-simulation framework is established to evaluate the hybrid control algorithm under nonlinear effects. Furthermore, a control test bench for the control surface transmission system is constructed to analyze the dynamic and static performance of the system under different control strategies and input commands. The experimental results show that, compared with the PID control, the hybrid control method reduces the steady-state error and vibration amplitude of the step response displacement by 51% and 75%, respectively, and decreases the amplitude of speed fluctuations by 75%. For the sinusoidal response, the displacement lag is reduced by 76%, and the amplitude of speed fluctuations is reduced by 50%.
ISSN:2076-0825
DOI:10.3390/act14110526
Fuente:Advanced Technologies & Aerospace Database