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US 12,719,398 B2Granted
Independent mitigation for isolation of electric motor
AssigneePratt & Whitney Canada Corp.
InventorsAlireza Gharagozloo, Michael Hanna
Life of this patent
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Abstract
A hybrid electric aircraft propulsion system includes both a turbine engine and an electric motor. A power management system controls operation of the electric motor and a pitch angle of a propeller associated with the propulsion system. A disconnect switch is provided to isolate the electric motor by mechanical decoupling the electric motor from the aircraft propulsion system.
Claims14
A power management system for a hybrid electric aircraft propulsion system including a turbine engine and an electric motor, the power management system comprising:
- a controller including a memory device coupled to a processor, wherein the memory device includes a stored program with instructions executable by the processor, wherein the stored program includes instructions for operating the electric motor;
- a propeller control configured to generate a signal communicated to the controller for controlling a pitch angle of a propeller associated with the aircraft propulsion system;
- and
- a disconnect switch configured to trigger a mechanical decoupling device to mechanically decouple the electric motor from the aircraft propulsion system, wherein the disconnect switch is configured to trigger the mechanical decoupling independent of the controller;
- and
- a power control lever generating a signal communicated to the controller for controlling operation of the turbine engine and the electric motor, wherein the disconnect switch is mounted to the power control lever.
3 more elements
A hybrid electric aircraft propulsion system comprising:
- a turbine engine configured to generate a first mechanical power output from a combustion process to drive a propeller;
- an electric motor configured to generate a second mechanical power output to drive the propeller;
- a selectively operable mechanical decoupling device for mechanically decoupling the electric motor from the propeller;
- a power management system comprising:
- a controller including a memory device coupled to a processor, wherein the memory includes a stored program with instructions executable by the processor, wherein the stored program includes instructions for operating the turbine engine and the electric motor;
- a propeller control configured to generate a signal communicated to the controller for controlling a pitch angle of the propeller;
- a disconnect switch configured to trigger the selectively operable mechanical decoupling device to mechanically decouple the electric motor from the aircraft propulsion system, wherein the disconnect switch is configured to trigger the mechanical decoupling independent of the controller;
- and
- a power control lever generating a signal communicated to the controller for controlling operation of the turbine engine and the electric motor, wherein the disconnect switch is mounted to the power control lever.
6 more elements
Dependencies are inferred from the claim text.