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
2025-07-31
Patent
Electronic Resource
English
Structurally integrated thermal management system for aerospace vehicles
European Patent Office | 2018
|STRUCTURALLY INTEGRATED THERMAL MANAGEMENT SYSTEM FOR AEROSPACE VEHICLES
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