Detachable power tethering systems for aircraft

1. An electric power tethering system for an aircraft having a plurality of rotor systems, the aircraft convertible between a vertical takeoff and landing flight mode in which the rotor systems provide thrust-borne lift and a forward flight mode in which the rotor systems provide forward thrust, the vertical takeoff and landing flight mode including a takeoff phase and a hover phase, the system comprising:

a surface power source; and

a power tether having a surface end configured to couple to the surface power source and an aircraft end configured to couple to the aircraft, the power tether configured to transmit power from the surface power source to the aircraft in the takeoff phase and the hover phase;

wherein the power tether is detachable to decouple the surface power source from the aircraft in response to the aircraft converting from the vertical takeoff and landing flight mode to the forward flight mode.

2. The electric power tethering system as recited in claim 1 wherein the surface power source further comprises at least one of a power grid, a generator or a battery.

3. The electric power tethering system as recited in claim 1 wherein the surface power source further comprises a retraction spool configured to retract the power tether.

4. The electric power tethering system as recited in claim 1 wherein the surface power source further comprises a mobile surface power source configured to move along a surface while the power tether couples the mobile surface power source to the aircraft.

5. The electric power tethering system as recited in claim 4 further comprising a land vehicle to transport the mobile surface power source along a land surface.

6. The electric power tethering system as recited in claim 4 further comprising a water vehicle to transport the mobile surface power source along a water surface.

7. The electric power tethering system as recited in claim 1 wherein the surface end of the power tether is detachable from the surface power source in response to the aircraft converting from the vertical takeoff and landing flight mode to the forward flight mode.

8. An aircraft system comprising:

an eVTOL aircraft having a plurality of rotor systems, the aircraft convertible between a vertical takeoff and landing flight mode in which the rotor systems provide thrust-borne lift and a forward flight mode in which the rotor systems provide forward thrust, the vertical takeoff and landing flight mode including a takeoff phase and a hover phase;

a surface power source; and

a power tether having a surface end configured to couple to the surface power source and an aircraft end configured to couple to the aircraft, the power tether configured to transmit power from the surface power source to the aircraft in the takeoff phase and the hover phase;

wherein the power tether is detachable to decouple the surface power source from the aircraft in response to the aircraft converting from the vertical takeoff and landing flight mode to the forward flight mode.

9. The aircraft system as recited in claim 8 wherein the aircraft further comprises a power inlet configured to couple to the aircraft end of the power tether, the aircraft end of the power tether detachable from the power inlet of the aircraft in response to the aircraft converting from the vertical takeoff and landing flight mode to the forward flight mode.

10. The aircraft system as recited in claim 8 wherein the power tether is detachable to decouple the surface power source from the aircraft in response to a manual user command.

11. The aircraft system as recited in claim 8 wherein the power tether is detachable to decouple the surface power source from the aircraft in response to the power tether extending beyond a power tether extension distance threshold.

12. The aircraft system as recited in claim 8 wherein the power tether is detachable to decouple the surface power source from the aircraft in response to a power consumption of the aircraft falling below a tether power consumption threshold.

13. The aircraft system as recited in claim 8 wherein the aircraft further comprises an onboard battery configured to provide electric power.

14. The aircraft system as recited in claim 13 further comprising a power management module configured to allocate power input for the aircraft from the onboard battery and the surface power source in the takeoff phase and the hover phase.

15. The aircraft system as recited in claim 8 wherein the aircraft further comprises a retraction spool configured to retract the power tether.

16. A method for providing electric power in an aircraft system comprising:

attaching a surface power source to an electrically powered aircraft using a power tether, the aircraft having a plurality of rotor systems, the aircraft convertible between a vertical takeoff and landing flight mode in which the rotor systems provide thrust-borne lift and a forward flight mode in which the rotor systems provide forward thrust, the vertical takeoff and landing flight mode including a takeoff phase;

providing electric power to the aircraft from the surface power source via the power tether during the takeoff phase;

converting the aircraft from the vertical takeoff and landing flight mode to the forward flight mode; and

detaching the surface power source from the aircraft in response to the aircraft converting from the vertical takeoff and landing flight mode to the forward flight mode.

17. The method as recited in claim 16 wherein the vertical takeoff and landing flight mode includes a hover phase, further comprising:

providing power to the aircraft from the surface power source via the power tether during the hover phase.

18. The method as recited in claim 17 further comprising performing aircraft system checks of the aircraft during the hover phase while electric power is provided to the aircraft via the power tether.

19. The method as recited in claim 16 further comprising charging a battery onboard the aircraft from the surface power source via the power tether while the aircraft is on the ground.

20. The aircraft system as recited in claim 8 wherein the aircraft comprises a tiltrotor aircraft, the rotor systems each rotating in a generally horizontal plane in the vertical takeoff and landing flight mode and a generally vertical plane in the forward flight mode.