A hybrid emergency power unit for an aircraft comprises a controller, a generator-motor coupled to the controller, a hydraulic pump coupled to the generator-motor, a battery pack coupled to the controller, and a turbine coupled to the generator-motor. During a bleed air mode, the turbine and the generator-motor supply electricity to the controller, which is configured to rectify an output of the generator-motor for consumption by one or more electrical systems on the aircraft. During an augment mode, when bleed air provides insufficient power, the controller is configured to draw at least some power from the battery pack and convert the output of the generator-motor for consumption by the one or more electrical systems. During an emergency mode, the controller is configured to draw electricity from the battery pack and provide power to drive the generator-motor, which in turn drives the hydraulic pump and provides electrical power to aircraft systems.
ELECTRIC HYBRID EMERGENCY POWER UNIT
ELEKTRISCHE HYBRIDE NOTSTROMVERSORGUNG
UNITÉ D'ALIMENTATION ÉLECTRIQUE DE SECOURS HYBRIDE
2024-10-23
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |