The present invention relates to a system (10) for an aircraft (100), wherein the system comprises: an electric motor (12) configured for propulsion of the aircraft; at least one 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 by ram air cooling; 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.
AEROSPACE ELECTRIC PROPULSION THERMAL MANAGEMENT SYSTEM
WÄRMEVERWALTUNGSSYSTEM FÜR ELEKTRISCHEN LUFTFAHRTANTRIEB
SYSTÈME DE GESTION THERMIQUE DE PROPULSION ÉLECTRIQUE AÉROSPATIALE
2025-08-06
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
Springer Verlag | 2024
|TIBKAT | 1972
|SLUB | 2014
|TIBKAT | 2013
|