The present invention relates to a thermal management system (10) for a hybrid electric aircraft (100), wherein the system comprises: at least one aircraft unit (12) configured to be used in electric propulsion of the aircraft; a first fluid circuit (18) arranged to cool the at least one aircraft unit; an internal combustion engine (28); a second fluid circuit (30) for the internal combustion engine; and a heat exchanger (20), wherein the first fluid circuit is arranged to provide heating to the second fluid circuit via said heat exchanger.
AEROSPACE THERMAL MANAGEMENT SYSTEM
31.07.2025
Patent
Elektronische Ressource
Englisch
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