Abstract: 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.

Abstract: A system (10) for an aircraft (100), including an electric motor (12) configured for propulsion of the aircraft; a motor control unit (14); a first fluid cooling circuit (16) arranged to circulate a first fluid (18a-c) and comprising at least one first cooling channel (20) in the at least one motor control unit; a first heat exchanger (22) connected to the first fluid cooling circuit for providing cooling to the first fluid cooling circuit; a ram air inlet (24) arranged to provide cooling to the first heat exchanger; a second fluid cooling circuit (26) arranged to circulate a second fluid (28a-b) and comprising at least one second cooling channel (30) in the electric motor; and a second heat exchanger (32), wherein the first fluid cooling circuit is arranged to provide cooling or heating to the second fluid cooling circuit via the second heat exchanger.

Abstract: 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.