A control system for a hybrid electric powerplant of an aircraft can include a throttle controller configured to receive one or more power settings and to output a heat engine setting and an electric motor setting, a heat engine controller operatively connected to the throttle controller. The heat engine controller can be configured to receive the heat engine setting and to control a heat engine system as a function of the heat engine setting to control torque output by a heat engine. The system can include a heat engine protection module that is part of or connected to the heat engine controller and configured to provide one or more protection commands to directly control one or more heat engine protection systems. The system can include an electric motor controller operatively connected to the throttle controller. The electric motor controller can be configured to receive the electric motor engine setting and to control an electric motor system as a function of the electric motor setting to control torque output by an electric motor. The system can include an electric motor protection module that is part of or connected to the electric motor controller and configured to provide one or more protection commands to directly control one or more electric motor protection systems.
CONTROL SYSTEM FOR HYBRID ELECTRIC POWER PLANTS
SYSTEME DE CONTROLE DE GROUPES MOTOPROPULSEURS HYBRIDES-ELECTRIQUES
2021-11-15
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |