Hybrid propulsion systems for an electric aircraft
A hybrid propulsion system for an electric aircraft, the system including an electric aircraft including a fuselage. The fuselage including an energy source containing electric power. The electric aircraft further including at least a laterally extending element attached to the fuselage and extending laterally from the fuselage. The electric aircraft further including at least a propulsor electrically connected to the energy source. The system also including at least a power unit pod attached to the at least a laterally extending element and including an auxiliary power unit configured to generate electric power. The power unit pod also including a fuel tank in fluid communication with the auxiliary power unit and a power output line electrically connected to the energy source of the electric aircraft.
1. A hybrid propulsion system for an electric aircraft comprising:
an electric aircraft, the electric aircraft comprising:
a fuselage;
a laterally extending element, wherein:
the laterally extending element is attached to the fuselage; and
the laterally extending element extends laterally from the fuselage;
an energy source configured to store electric power;
a propulsor electrically connected to the energy source; and
a fuel tank; and
a power unit pod attached to the laterally extending element, the power unit pod comprising:
an auxiliary power unit in fluid communication with the fuel tank and configured to generate electric power;
a local controller communicatively connected to the auxiliary power unit, the fuel tank, and a flight controller onboard the electric aircraft;
a power supply electrically connected to the auxiliary power unit, the local controller, and the fuel tank, wherein the power supply is configured to use a source power power the local controller; and
a power output line electrically connected to the propulsor for powering the propulsor with the electric power generated by the auxiliary power unit.
2. The hybrid propulsion system of claim 1 , wherein the fuel tank is positioned within laterally extending element.
3. The hybrid propulsion system of claim 2 , wherein the laterally extending element and the power unit pod are in fluid communication through a fuel interface.
4. The hybrid propulsion system of claim 1 , wherein the local controller is configured to manage a temperature of the auxiliary power unit.
5. The hybrid propulsion system of claim 1 , wherein the local controller is configured to manage a temperature of the power supply.
6. The hybrid propulsion system of claim 1 , wherein the local controller is configured to transmit data to the flight controller.
7. The hybrid propulsion system of claim 1 , wherein the local controller is configured to transmit data to an interface for display to a pilot.
8. The hybrid propulsion system of claim 1 , wherein the fuel tank includes a fuel pump for transferring fuel from the fuel tank to the auxiliary power unit.
9. The hybrid propulsion system of claim 8 , wherein the local controller is configured to transmit a control signal to at least the fuel pump of the fuel tank to control operation of the fuel pump.
10. The hybrid propulsion system of claim 8 , wherein the power supply is configured to provide load power to the fuel tank including the fuel pump.
11. The hybrid propulsion system of claim 1 , wherein the power unit pod is detachable from the electric aircraft.
12. The hybrid propulsion system of claim 1 , wherein the power unit pod further comprises a predetermined voltage power line, the predetermined voltage power line electrically connected to the auxiliary power unit.
13. The hybrid propulsion system of claim 1 , wherein the propulsor further comprises:
a pusher propulsor, wherein the pusher propulsor is configured to provide forward thrust to the electric aircraft; and
a lift propulsor, wherein the lift propulsor is configured to provide lift to the electric aircraft.
14. The hybrid propulsion system of claim 1 , wherein the power unit pod is removably attached to an underside of the at least laterally extending element.
15. The hybrid propulsion system of claim 14 , wherein the power unit pod is connected to a pod support, wherein the pod support is removably attached to the underside of the laterally extending element.
16. The hybrid propulsion system of claim 15 , wherein the pod support has an airfoil cross section.
17. The hybrid propulsion system of claim 1 , wherein the laterally extending element comprises a lift generating body, wherein the lift generating body has an airfoil cross section.
18. The hybrid propulsion system of claim 1 , wherein the electric aircraft further comprises a first predetermined voltage interface, wherein the first predetermined voltage interface is electrically connected to:
the energy source;
the propulsor; and
the power output line of the at unit pod.
19. The hybrid propulsion system of claim 18 , wherein the first predetermined voltage interface is configured to:
receive a first predetermined voltage power from the energy source and the power output line of the power unit pod; and
provide power to the propulsor.
20. The hybrid propulsion system of claim 13 , wherein:
the lift propulsor comprises two lift propulsors; and
each of the two lift propulsors are connected to the laterally extending element.
21. The hybrid propulsion system of claim 13 , wherein the electric aircraft further comprises:
a first propulsor boom connected to the laterally extending element; and
a second propulsor boom connected to the laterally extending element.
22. The hybrid propulsion system of claim 21 , wherein the lift propulsor comprises:
a first lift propulsor connected to the first propulsor boom; and
a second lift propulsor connected to the second propulsor boom.
23. The hybrid propulsion system of claim 21 , wherein the lift propulsor comprises:
a first set of lift propulsors connected to the first propulsor boom; and
a second set of lift propulsors connected to the second propulsor boom.
24. The hybrid propulsion system of claim 13 , wherein the pusher propulsor is connected to a tail end of the electric aircraft.
25. The hybrid propulsion system of claim 1 , wherein the power unit pod is contained within a nacelle, wherein the nacelle is shaped to reduce drag when in edgewise flight.
26. The hybrid propulsion system of claim 1 , wherein the electric aircraft comprises a flight controller.
27. The hybrid propulsion system of claim 26 , wherein the flight controller is communicatively connected to the auxiliary power unit of the power unit pod.
28. The hybrid propulsion system of claim 1 , wherein the auxiliary power unit of the at least power unit pod has a power rating of over 100 kW.
29. The hybrid propulsion system of claim 1 , wherein the auxiliary power unit of the power unit pod has a power rating in a range of 150 to 200 kW.
30. The hybrid propulsion system of claim 19 , wherein the electric aircraft further comprises a second predetermined voltage interface, wherein:
the second predetermined voltage interface is electrically connected to:
the energy source;
the propulsor; and
the power output line of the power unit pod; and
the second predetermined voltage interface is configured to:
receive a second predetermined voltage power from the energy source and the power output line of the power unit pod; and
provide power to the propulsor.
31. The hybrid propulsion system of claim 1 , wherein the power supply is further configured to use the source power from the auxiliary power unit to power the local controller.