Abstract
Nowadays, the reduction of aircraft emissions is one of the industrial targets with a horizon time until 2050. The recent progresses in electrical drives give the opportunity to modify the aircraft propulsion based on thermal engine or gas turbine to a hybrid/full electric one. Some problems must be solved: weight, reliability, and the choice of the best configuration for the electric propulsion. One of the most important aspects to solve is the thermal behavior of power converters and electric motors. This paper proposes an optimization procedure for the design of surface permanent magnet motors used for the aircraft propulsion: the aim of the paper is to investigate the possibility of cooling the motor with only the air flow due to the aircraft speed. The optimization procedure has been solved with the integration of analytical model and finite element analysis and using a differential evolution algorithm.
Highlights
The rapid growing of civil air traffic in last decades determined the start of different initiatives [1]with the aim to reduce aircraft emissions in the atmosphere
This paper proposes an optimization procedure for the design of surface permanent magnet motors used for the aircraft propulsion: the aim of the paper is to investigate the possibility of cooling the motor with only the air flow due to the aircraft speed
The optimization procedure has been solved with the integration of analytical model and finite element analysis and using a differential evolution algorithm
Summary
The rapid growing of civil air traffic in last decades determined the start of different initiatives [1]. An alternative to the liquid cooling could be the use of forced convection due to the air flow generated by the aircraft speed and the propellers; obviously, this determines a reduction of power density but with an overall increase of reliability and reduction of the on-board volume occupation. In this paper is proposed a design methodology able to investigate the use of forced convection due to the air flow for electric motors used for the propulsion of hybrid/full electric aircraft. The approach starts from the solution of heat problem for the calculation of an appropriate heat exchange coefficient and using the magneto-thermal finite element analysis, a sizing methodology for forced air cooled motor is developed. The optimal sizing procedure is solved using a differential evolution algorithm
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