Vertical take-off and landing (VTOL) aircraft

1. A vertical take-off and landing (VTOL) aircraft, wherein the aircraft comprises:

at least a lift component affixed to the aft end of a boom, wherein the lift component is configured to generate lift;

a fuselage comprising a fore end and an aft end wherein the fuselage further comprises a geodesic construction wherein the geodesic construction further comprises stringers wound about station frames in opposing spiral directions; and

a tail affixed to the aft end of a fuselage, wherein the tail comprises:

a plurality of vertically projecting elements, wherein the plurality vertically projecting elements are affixed at the aft end of the boom; and

the plurality of vertically projecting elements are positioned outside of the wake from the at least a lift component while the aircraft is engaged in conventional flight.

2. The aircraft of claim 1 , wherein the aircraft is an electric aircraft.

3. The aircraft of claim 1 , wherein the aircraft further includes a thrust component configured to generate thrust.

4. The aircraft of claim 3 , wherein the aircraft further includes a flight controller configured to control the thrust component.

5. The aircraft of claim 3 , wherein the aircraft further comprises the thrust component mounted to aft end of fuselage.

6. The aircraft of claim 1 , wherein the plurality of vertically projecting elements comprise:

a first vertically projecting element positioned to a first side of the fuselage; and

a second vertically projecting element positioned to a second side of the fuselage.

7. The aircraft of claim 6 , wherein the plurality of vertically projecting elements are configured to be in a V-shaped geometry.

8. The aircraft of claim 1 , wherein the plurality of vertically projecting elements form an angle relative a longitudinal plane of the aircraft.

9. The aircraft of claim 1 , wherein the plurality of vertically projecting elements form a sweep angle relative a lateral plane of the aircraft.

10. The aircraft of claim 1 , wherein the aircraft further includes a plurality of fixed wings configured to generate lift, wherein the plurality of fixed wings are attached to the fuselage.

11. The aircraft of claim 10 , wherein the plurality of fixed wings includes:

a first wing attached to a first side of the fuselage; and

a second wing attached to a second side of the fuselage.

12. The aircraft of claim 11 , wherein the boom comprises:

a first boom comprising a first rear end affixed to the tail and a first forward end proximal to the fore end of the fuselage, wherein the first boom is affixed to the first wing; and

a second boom including a second rear end affixed to the tail and a second forward end proximal to a fore end of the fuselage, wherein the second boom is affixed to the second wing.

13. The aircraft of claim 10 , wherein the plurality of fixed wings are mechanically attached to the boom.

14. The aircraft of claim 1 , wherein the aircraft further comprises at least a control surface located on the plurality of vertically projecting elements.

15. The aircraft of claim 1 , wherein the at least a control surface comprises a plurality of redundant control surfaces.

16. The aircraft of claim 15 , wherein:

the first vertically projecting element further comprises at least a first rudder: and the second vertically projecting element further comprises at least a second rudder.

17. The aircraft of claim 1 , wherein the thrust element comprises a pusher propeller disposed laterally between two vertical fins from the plurality of vertically projecting elements.

18. The aircraft of claim 1 , wherein the aircraft further includes a flight controller configured to operate the at least a lift component.

19. The aircraft of claim 1 , wherein the lift component comprises at least a electric motor, wherein the at least a electric motor is recessed in the boom.