Thermal evaluation of a propulsion motor for electric air-craft

• The axial flux and the radial flux machine with concentrated winding are compared in an electric aircraft application. New materials for impregnating the windings are investigated thermally and the radial flux machine is investigated in a case with direct air flow cooling.The axial flux machine has higher relative amount of copper in the end windings and the copper losses are higher in this machine type. However the two rotor concept with a central stator without a yoke has lower core losses. An axial flux machine where the core losses dominate could have benefits compared to the radial flux machine. An impregnating material with the thermal conductivity of 1 W/mK results in only 35 degrees temperature increase over the core temperature of the winding when the current density is 18.8 A / mm2. An example design of the machine is shown. The losses can according to the Comsol analysis be handled with free airflow the machine parts.

Ämnesord

TEKNIK OCH TEKNOLOGIER  -- Maskinteknik -- Rymd- och flygteknik (hsv//swe)

ENGINEERING AND TECHNOLOGY  -- Mechanical Engineering -- Aerospace Engineering (hsv//eng)

TEKNIK OCH TEKNOLOGIER  -- Maskinteknik -- Energiteknik (hsv//swe)

ENGINEERING AND TECHNOLOGY  -- Mechanical Engineering -- Energy Engineering (hsv//eng)

TEKNIK OCH TEKNOLOGIER  -- Elektroteknik och elektronik -- Annan elektroteknik och elektronik (hsv//swe)

ENGINEERING AND TECHNOLOGY  -- Electrical Engineering, Electronic Engineering, Information Engineering -- Other Electrical Engineering, Electronic Engineering, Information Engineering (hsv//eng)

Nyckelord

Aircraft propulsion

FEA

Permanent electric motor

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