Applied Automation and Industrial Diagnostics Lab (LAADI), University of Djelfa, Djelfa, Algeria.
Department of Avionics Engineering, CAE, National University of Sciences & Technology (NUST), Islamabad, Pakistan.
PLoS One. 2023 Jul 7;18(7):e0283541. doi: 10.1371/journal.pone.0283541. eCollection 2023.
This paper describes a robust performance comparison of flight control actuation controllers based on a permanent magnet synchronous motor (PMSM) in more electric aircraft (MEA). Recently, the PMSM has become a favorite for the flight control applications of more electric aircraft (MEA) due to their improved efficiency, higher torque, less noise, and higher reliability as compared to their counterparts. Thus, advanced nonlinear control techniques offer even better performance for the control of PMSM as noticed in this research. In this paper, three nonlinear approaches i.e. Feedback Linearization Control (FBL) through the cancellation of the non-linearity of the system, the stabilization of the system via Backstepping Control (BSC) using the Lyapunov candidate function as well as the robust performance with chattering minimization by applying the continuous approximation based Sliding Mode Control (SMC) are compared with generalized Field-Oriented Controller (FOC). The comparison of FOC, FBL, BSC and SMC shows that the nonlinear controllers perform well under varying aerodynamic loads during flight. However, the performance of the sliding mode control is found superior as compared to the other three controllers in terms of better performance characteristics e.g. response time, steady-state error etc. as well as the control robustness in the presence of the uncertain parameters of the PMSM model and variable load torque acting as a disturbance. In essence, the peak of the tolerance band is less than 20% for all nonlinear and FOC controller, while it is less than 5% for SMC. Steady state error for the SMC is least (0.01%) as compared to other three controllers. Moreover, the SMC controller is able to withstand 50% parameter variation and loading torque of 10 N.m without significant changes in performance. Six simulation scenarios are used to analyze the performance and robustness which depict that the sliding mode controller performs well in terms of the desired performance for MEA application.
本文描述了基于永磁同步电机（PMSM）在多电飞机（MEA）中飞行控制致动器的鲁棒性能比较。最近，由于与同类产品相比，PMSM 具有提高的效率、更高的扭矩、更少的噪音和更高的可靠性，因此成为多电飞机（MEA）飞行控制应用的首选。因此，如本研究中所注意到的，先进的非线性控制技术为 PMSM 的控制提供了更好的性能。在本文中，三种非线性方法，即通过系统非线性消除的反馈线性化控制（FBL）、通过 Lyapunov 候选函数稳定系统的反向步控制（BSC）以及通过应用基于连续逼近的滑模控制（SMC）减小抖振的鲁棒性能，与广义磁场定向控制（FOC）进行了比较。FOC、FBL、BSC 和 SMC 的比较表明，非线性控制器在飞行过程中在变化的空气动力负载下表现良好。然而，与其他三个控制器相比，滑模控制的性能优越，具有更好的性能特性，例如响应时间、稳态误差等，以及在存在 PMSM 模型的不确定参数和作为干扰的可变负载扭矩的情况下的控制鲁棒性。本质上，所有非线性和 FOC 控制器的容差带峰值均小于 20%，而 SMC 的容差带峰值小于 5%。与其他三个控制器相比，SMC 的稳态误差最小（0.01%）。此外，SMC 控制器能够承受 50%的参数变化和 10 N.m 的负载扭矩，而性能没有明显变化。使用六个仿真场景来分析性能和鲁棒性，表明滑模控制器在 MEA 应用的期望性能方面表现良好。
