A hybrid electric engine control module (ECU) configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system. The ECU can be configured to receive a torque command and split output power between the electric motor system and the heat engine system. Additionally and/or alternatively, the ECU can be configured to balance a total torque against a second total torque of a second aircraft powerplant.
TORQUE BALANCING FOR HYBRID ELECTRIC PROPULSION SYSTEMS AND AIRCRAFT UTILIZING HYBRID ELECTRIC PROPULSION SYSTEMS
DREHMOMENTAUSGLEICH FÜR HYBRIDE ELEKTRISCHE ANTRIEBSSYSTEME UND FLUGZEUG MIT HYBRIDEN ELEKTRISCHEN ANTRIEBSSYSTEMEN
ÉQUILIBRAGE DE COUPLE POUR SYSTÈMES DE PROPULSION ÉLECTRIQUE HYBRIDES ET AÉRONEF UTILISANT DES SYSTÈMES DE PROPULSION ÉLECTRIQUE HYBRIDES
2022-11-23
Patent
Electronic Resource
English
European Patent Office | 2020
|European Patent Office | 2020
|European Patent Office | 2020
|Hybrid-Electric Propulsion Systems for Aircraft
AIAA | 2013
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