Sizing approach of high torque density motors for aircraft application

Dannier, Adolfo; Fedele, Emanuele; Coppola, M.

doi:10.1109/speedam48782.2020.9161871

Cited by 8 publications

(1 citation statement)

References 26 publications

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“…The aim is to obtain electric machines with high power density and torque. To achieve this goal a new design approach can be adopted: starting from the mathematical model of the electric machine a suitable relation between the requested torque and the required volume is needed [17]. The most promising machines that bring the main requirements of an electric traction motor in terms of high power density, high torque density, high speed range, high efficiency, high reliability and low costs is definitely represented by motors Obviously, based on this choice in order to obtain high performance, it is necessary use a combined cooling system, where air and water have been used, so as to ensure the correct disposal of the different rates of energy losses mainly attributable to Joule losses.…”

Section: Electric Motor/generator and Cooling Systemmentioning

confidence: 99%

A Comparative Assessment of Hybrid Parallel, Series, and Full-Electric Propulsion Systems for Aircraft Application

2022

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This article presents a preliminary suitable sizing methodology for the design process of the powertrain architecture for a hybrid-electric propulsion system for ultra-light and general aviation aircraft. The main objective of this activity is to design and realize a prototype of a hybrid-electric propulsion system for Cessna 337 aircraft with a maximum take-off power of 134 kW. At the same mission, two operating strategies have been chosen, max recharge and max efficiency. Where, in the first case the engine runs at wide-open throttle to quickly charge the battery, while for the second run at minimum specific consumption to reduce consumption. The primary energy assessment has been conducted in all proposed propulsion configurations with the same aircraft, mission, and maximum take-off weight. The results also indicated that parallel hybrid propulsion shows a better compromise in terms of 10% energy saving, 4% CO2 reduction, and mission duration.

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Section: Electric Motor/generator and Cooling Systemmentioning

confidence: 99%