An example hybrid aircraft propulsion system (2B) includes a plurality of electrical busses (4) comprising a propulsion bus (4A), a critical bus (4B), and a non-critical bus (4C); an electrical energy storage system (34B) coupled to each of the plurality of electrical busses (4); one or more power units (6) configured to generate and output electrical energy via the propulsion bus (4A); one or more electrical machines (14A, 14B) configured to drive respective propulsors (16A, 16B) using electrical energy received via the propulsion bus (4A); one or more hotel loads (50) configured to receive energy via the non-critical bus (4C); and one or more critical loads configured to receive energy via the critical bus (4B).
ELECTRICAL ARCHITECTURE FOR HYBRID PROPULSION
ELEKTRISCHE ARCHITEKTUR FÜR HYBRIDANTRIEB
ARCHITECTURE ÉLECTRIQUE POUR PROPULSION HYBRIDE
11.08.2021
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |