Design and Experimental Analysis on the Control System of High Reliability Fault Tolerant Permanent Magnet Motor Used in Electric Actuator

HAO Zhenyang; HU Yuwen

doi:10.7527/S1000-6893.2013.0017

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2013 , Vol. 34 >Issue 1: 141 - 152

DOI: https://doi.org/10.7527/S1000-6893.2013.0017

Electronics and Control

Design and Experimental Analysis on the Control System of High Reliability Fault Tolerant Permanent Magnet Motor Used in Electric Actuator

HAO Zhenyang ,
HU Yuwen

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Jiangsu Province Key Laboratory of New Energy Generation and Power Conversion, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received date: 2012-01-20

Revised date: 2012-02-24

Online published: 2013-01-19

Supported by

China Postdoctoral Science Foundation (20110491408); Aeronautical Science Foundation of China (2011ZC52039)

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Abstract

For the six-phase-ten-pole fault tolerant permanent magnet motor (FTPMM) with a centrifugal permanent magnet on the surface of its rotor, a strong fault tolerant system is proposed and realized with the current direct control strategy to improve the reliability of the electric actuator with the motor. Without fault diagnosis and algorithm switching, this method enables the motor speed to remain invariant. Motor output power corresponds to the number of phases which fail, i.e., with one, two, and three phases broken down the motor output will be respectively 100%, 80%, and 60% of the rated power. A 750 W principle prototype of the fault tolerant permanent magnet motor with a digital controller is designed and tested. The experiment results validate the theoretical prediction and show the strong fault tolerant capacity and feasibility of the whole control system.

Key words： fault tolerance; permanent magnet motor; current direct control; open-circuit fault; short-circuit fault

Cite this article

HAO Zhenyang , HU Yuwen . Design and Experimental Analysis on the Control System of High Reliability Fault Tolerant Permanent Magnet Motor Used in Electric Actuator[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2013 , 34(1) : 141 -152 . DOI: 10.7527/S1000-6893.2013.0017

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