An electrical power unit cooling system including at least one cooling fin configured to be thermally connected to a bus housing of the electrical power unit, the bus housing being configured to be attached to a surface of an aircraft fan housing such that the at least one cooling fin protrudes through the fan housing in order to be cooled by air flow within the fan housing.
AIRCRAFT POWER ELECTRONIC UNIT AND METHOD OF COOLING
2020-12-03
Patent
Elektronische Ressource
Englisch
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