Fault tolerant hybrid electric propulsion system for an aerial vehicle
Hybrid electric propulsion systems includes a combustion engine and an electric motor. The hybrid electric propulsion systems may include or utilize a non-transitory computer-readable medium comprising computer-executable instructions, which when executed by a processor associated with the hybrid electric propulsion system, cause the processor to perform a method that includes determining an occurrence of a thrust asymmetry in the hybrid electric propulsion system, and controlling the electric motor to decrease an efficiency of the electric motor for a transient time period sufficient to reduce a torque output of the combustion engine to match an electrical load on the combustion engine.
1. A non-transitory computer-readable medium comprising computer-executable instructions, which when executed by a processor associated with a hybrid electric propulsion system for an aerial vehicle, cause the processor to perform a method comprising:
determining an occurrence of a thrust asymmetry in the hybrid electric propulsion system, the hybrid electric propulsion system comprising a combustion engine and an electric motor; and
controlling the electric motor to decrease an efficiency of the electric motor for a transient time period sufficient to reduce a torque output of the combustion engine to match an electrical load on the combustion engine.
2. The non-transitory computer-readable medium of claim 1 , wherein determining the occurrence of the thrust asymmetry comprises determining a change in the electrical load on the combustion engine that exceeds an electrical load rate threshold, the electrical load rate threshold selected based at least in part on an overspeed limit for the electric motor.
3. The non-transitory computer-readable medium of claim 1 , wherein the thrust asymmetry comprises or is attributable to at least one of:
a rapid change in the electrical load;
a loss of torque generation from the electric motor;
a rapid increase in thrust produced by a propulsion assembly of the hybrid electric propulsion system; or
a rapid decrease in thrust produced by the propulsion assembly of the hybrid electric propulsion system.
4. The non-transitory computer-readable medium of claim 1 , wherein the computer-executable instructions, when executed by the processor, cause the processor to further perform the method, including:
changing a delivery of electrical power within the hybrid electric propulsion system for at least a portion of the transient time period.
5. The non-transitory computer-readable medium of claim 4 , wherein changing the delivery of electrical power within the hybrid electric propulsion system comprises at least one of:
changing a first delivery of electrical power to an energy storage device;
changing a second delivery of electrical power to an electrical braking system; or
changing a third delivery of electrical power to an accessory load.
6. The non-transitory computer-readable medium of claim 1 , wherein the computer-executable instructions, when executed by the processor, cause the processor to further perform the method, including:
reducing the torque output of the combustion engine to match the electrical load on the combustion engine.
7. The non-transitory computer-readable medium of claim 6 , wherein reducing the torque output of the combustion engine comprises transiently sinking electrical power from the combustion engine.
8. The non-transitory computer-readable medium of claim 6 , wherein reducing the torque output of the combustion engine comprises at least one of:
reducing a fuel flow to the combustion engine for at least a portion of the transient time period;
activating one or more variable geometry components of the combustion engine; or
activating a physical braking system mechanically coupled with the combustion engine.
9. The non-transitory computer-readable medium of claim 1 , wherein the combustion engine comprises: a gas turbine engine, a piston engine, or a rocket engine.
10. A controller for a hybrid electric propulsion system of an aerial vehicle, the controller comprising:
a non-transitory computer-readable medium; and
a processor;
wherein the non-transitory computer-readable medium comprises computer-executable instructions, which when executed by the processor, cause the processor to perform a method comprising:
determining an occurrence of a thrust asymmetry in the hybrid electric propulsion system, the hybrid electric propulsion system comprising a combustion engine and an electric motor; and
controlling the electric motor to decrease an efficiency of the electric motor for a transient time period sufficient to reduce a torque output of the combustion engine to match an electrical load on the combustion engine.
11. The controller of claim 10 , wherein determining the occurrence of the thrust asymmetry comprises determining a change in the electrical load on the combustion engine that exceeds an electrical load rate threshold, the electrical load rate threshold selected based at least in part on an overspeed limit for the electric motor.
12. The controller of claim 10 , wherein the thrust asymmetry comprises or is attributable to at least one of:
a rapid change in the electrical load;
a loss of torque generation from the electric motor;
a rapid increase in thrust produced by a propulsion assembly of the hybrid electric propulsion system; or
a rapid decrease in thrust produced by the propulsion assembly of the hybrid electric propulsion system.
13. The controller of claim 10 , wherein the computer-executable instructions, when executed by the processor, cause the processor to further perform the method, including:
changing a delivery of electrical power within the hybrid electric propulsion system for at least a portion of the transient time period.
14. The controller of claim 13 , wherein changing the delivery of electrical power within the hybrid electric propulsion system comprises at least one of:
changing a first delivery of electrical power to an energy storage device;
changing a second delivery of electrical power to an electrical braking system; or
changing a third delivery of electrical power to an accessory load.
15. The controller of claim 10 , wherein the computer-executable instructions, when executed by the processor, cause the processor to further perform the method, including:
reducing the torque output of the combustion engine to match the electrical load on the combustion engine.
16. The controller of claim 15 , wherein reducing the torque output of the combustion engine comprises transiently sinking electrical power from the combustion engine.
17. The controller of claim 15 , wherein reducing the torque output of the combustion engine comprises at least one of:
reducing a fuel flow to the combustion engine for at least a portion of the transient time period;
activating one or more variable geometry components of the combustion engine; or
activating a physical braking system mechanically coupled with the combustion engine.
18. The controller of claim 10 , wherein the combustion engine comprises: a gas turbine engine, a piston engine, or a rocket engine.
19. A hybrid electric propulsion system for an aerial vehicle, the hybrid electric propulsion system comprising:
a combustion engine;
an electric motor; and
a controller, the controller comprising a non-transitory computer-readable medium and a processor;
wherein the non-transitory computer-readable medium comprises computer-executable instructions, which when executed by the processor, cause the processor to perform a method comprising:
determining an occurrence of a thrust asymmetry in the hybrid electric propulsion system; and
controlling the electric motor to decrease an efficiency of the electric motor for a transient time period sufficient to reduce a torque output of the combustion engine to match an electrical load on the combustion engine.
20. The hybrid electric propulsion system of claim 19 , wherein the combustion engine comprises: a gas turbine engine, a piston engine, or a rocket engine.