Mechanism Analysis and Optimum Control of Negative Airgap Eccentricity Effect for in-wheel Switched Reluctance Motor Driving System

This paper analyzes the generation and influence mechanism of negative airgap eccentricity effect for in-wheel switched reluctance motor (SRM) driving system, and proposes an optimum control strategy to achieve cooperative optimal performance between in-wheel motor driving system and electric vehicle (EV). Firstly, the electromagnetic characteristic of SRM under airgap eccentricity is studied based on electromagnetic coupling model and circuit driving equation. Then, the negative effect of airgap eccentricity on the in-wheel SRM driving system is analyzed in timefrequency domain combined on the excitation characteristics of unbalanced radial force. Finally, an independent current chopping control strategy for in-wheel SRM driving system based on vehicle vibration feedback is proposed, and the controller parameters are optimized by interpolation. The simulation results show that the proposed optimum control strategy can improve the driving torque while restrain the unbalanced radial force, and effectively suppress the negative airgap eccentricity effect of in-wheel motor driving system. This study starts from the dynamics relationship between SRM, in-wheel motor driving system and EV, and lays a theoretical foundation for solving the negative dynamic effect of in-wheel motor driving system.

Synthesis of an active flutter suppression system in the transonic domain using a computational model

ABSTRACT Control laws for implementing active flutter suppression are generally derived from linear aeroelastic models. In this paper, families of control laws for implementing an active flutter suppression system were initially designed using linearised aeroelastic models based on the doublet lattice method after ignoring the aerodynamic loads associated with relatively faster time scales. Using these preliminary sets of control laws and the nonlinear transonic small disturbance theory, near-optimum control laws were chosen in the transonic domain to maximally increase the flutter speed of a typical aircraft wing by at least 16% or more. Thus it is shown that it is feasible to systematically design near-optimal control laws for active flutter suppression using computational models in transonic flow. The doublet lattice method coupled with the zeroth-order matrix Padé approximant provided the fastest method for synthesising a large number of preliminary control laws. The methodology was successfully demonstrated by applying it to two benchmarking examples.

NUMERICAL ALGORITHM OF COMPUTATIONAL EXPERIMENT OF THE APPLIED OPTIMAL CONTROL PROBLEM IN SYSTEMS WITH DISTRIBUTED PARAMETERS

Stages of computing experiment of the developed algorithm by means of the final and differential scheme for the solution of applied problems of optimum control of the processes described by the solutions of elliptic type are given n article.