An aircraft hybrid electrical propulsion (HEP) system (100) includes an electrical system configured to deliver power to a plurality of electrical loads, a propulsion system (205) configured to generate thrust in response to an input power, and an HEP controller (200) in signal communication with the electrical system and the propulsion system (205). The HEP controller (200) is configured to monitor a load demand of at least one electrical load among the plurality of electrical loads and to actively control the input power to actively control the thrust in response to changes in the load demand.
AIRCRAFT HYBRID ELECTRIC PROPULSION ARCHITECTURE ENABLING MODES OF OPERATION
HYBRIDE ELEKTROANTRIEBSARCHITEKTUR FÜR FLUGZEUGE ZUR ERMÖGLICHUNG VON BETRIEBSMODI
ARCHITECTURE DE PROPULSION ÉLECTRIQUE HYBRIDE D'AÉRONEF PERMETTANT DES MODES DE FONCTIONNEMENT
2024-09-11
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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