Abstract
The present trend of aerospace industries is being shifted towards a “More Electric Aircraft” system which needs to be high power dense. For this purpose, the integration technologies have gained massive interest, providing the benefits of reduced losses, weight, volume and cost. In this article, the integration concept of a passive filter inductor is presented for a permanent magnet synchronous motor. The integrated motor eliminates the need of an external inductor, thus, eliminates the added inductor losses, mass, volume and cost associated with it. The motor utilizes its’s inherent inductance to use it as a filter inductor instead of implementing a discrete inductor that is commonly placed between inverter and the motor terminals. Optimization study is carried out, where the filter branch windings are tapped, in terms of improving mass and volume and performance parameters such as power losses and torque ripple. From the optimization study, the motor with minimum weight and volume is experimentally validated at the rated conditions, in order to prove the concept feasibility. Total system weight and volume of integrated and traditional motor drives are compared, which gives the minimum weight of 2.26 kg and 3.14 kg respectively, and the minimum volume of 0.54 L and 1.1 L respectively.
Highlights
Motor Drive ApplicationThe target application is a helicopter electro-mechanical actuation system (HEMAS). that provides the fault tolerance of individual jamming of an actuator whilst replacing the hydraulic actuator of a modern fly-by-wire hydraulic primary flight control system
Introduction published maps and institutional affilThe continuous development of aircraft transportation, the demand for performance optimization and the need of reducing both weight and volume have pushed the aerospace industries to shift toward “More Electric Aircraft”
The number of turns in the filter branch windings will reduce through the tapings, depending on the filter branch inductance, and the left-over motor turns will be added to the motor branch after connecting the filter capacitor and damping resistor
Summary
The target application is a helicopter electro-mechanical actuation system (HEMAS). that provides the fault tolerance of individual jamming of an actuator whilst replacing the hydraulic actuator of a modern fly-by-wire hydraulic primary flight control system. The target application is a helicopter electro-mechanical actuation system (HEMAS). That provides the fault tolerance of individual jamming of an actuator whilst replacing the hydraulic actuator of a modern fly-by-wire hydraulic primary flight control system. Each actuator is driven by a fault-tolerant PM machine, as shown, fed through individual inverters. The system provides the required performance after a mechanical damage or failure of a component (i.e., freewheel or jam) or two failures of electrical/electronic components (i.e., power electronics converter or motor). To accommodate a mechanical failure of the output mechanism a disconnect device is required to decouple an actuator in case of a jam or freewheel [18,19]
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