In-flight reconfigurable hybrid unmanned aerial vehicle
This disclosure is directed to an unmanned aerial vehicle (“UAV”) that transitions in-flight between vertical flight configuration and horizontal flight configuration by changing an orientation of the UAV by approximately ninety degrees. The UAV may include propulsion units that are coupled to a wing. The wing may include wing segments rotatably coupled together by pivots that rotate to position the propulsion units around a center of mass of the UAV when the fuselage is oriented perpendicular with the horizon. In this vertical flight configuration, the UAV may perform vertical flight or hover. During the vertical flight, the UAV may cause the wing to extend outward via the pivots such that the wing segments become positioned substantially parallel to one another and the wing resembles a conventional fixed wing. With the wing extended, the UAV assumes a horizontal flight configuration that provides upward lift generated from the wing.
1. An aircraft, comprising:
a fuselage;
opposed wings extending from opposed sides of the fuselage;
at least one engine mounted to each of the opposed wings;
wherein at least a portion of each opposed wing including the at least one engine rotates relative to the fuselage around a rotation axis, and wherein the at least one engine has a propeller with a plurality of blades configured for a pitch variation.
2. The aircraft according to claim 1 , wherein the rotation axis is non-perpendicular to a longitudinal axis of the fuselage.
3. The aircraft according to claim 1 , wherein at least the portion of each opposed wing including the at least one engine rotates relative to the fuselage between a first configuration adapted for vertical take-off and landing, and a second configuration adapted for horizontal flight.
4. The aircraft according to claim 3 , wherein the at least one engine provides lift to the aircraft in the first configuration.
5. The aircraft according to claim 3 , wherein the pitch variation of the plurality of propeller blades allows hovering in the first configuration of the opposed wings.
6. The aircraft according to claim 3 , wherein the pitch variation of the plurality of propeller blades allows forward flight in the second configuration of the opposed wings.
7. The aircraft according to claim 1 , wherein output of each engine is independently adjustable.
8. The aircraft according to claim 1 , wherein each of the opposed wings includes a fixed portion extending from the fuselage and a rotating portion outboard of the fixed portion.
9. The aircraft according to claim 8 , wherein a leading edge of the rotating portion of each opposed wing faces upward in the first configuration of the opposed wings.
10. The aircraft according to claim 8 , wherein each of the opposed wings has at least one actuator to control rotation of the rotating portion relative to the fixed portion.
11. The aircraft according to claim 10 , wherein the at least one actuator is a linear actuator.
12. An aircraft, comprising:
a fuselage;
opposed wings extending from opposed sides of the fuselage;
a plurality of engines mounted to each of the opposed wings;
wherein at least a portion of each opposed wing including the plurality of engines rotates relative to the fuselage around a rotation axis that is non-perpendicular to a longitudinal axis of the fuselage between a first configuration adapted for vertical take-off and landing, and a second configuration adapted for horizontal flight, and
wherein an output of each engine is independently adjustable at least in the first configuration.
13. The aircraft according to claim 12 , wherein the output of each engine is independently adjustable by varying a speed of each engine.
14. The aircraft according to claim 12 , wherein the plurality of engines provide lift to the aircraft in the first configuration.
15. The aircraft according to claim 12 , wherein each of the opposed wings includes a fixed portion extending from the fuselage and a rotating portion outboard of the fixed portion.
16. The aircraft according to claim 15 , wherein a leading edge of the rotating portion of each opposed wing faces upward in the first configuration of the opposed wings.
17. A method of flying an aircraft, the method comprising:
rotating at least a portion of opposed wings relative to a fuselage around a rotation axis that is non-perpendicular to a longitudinal axis of the fuselage to orient a leading edge of each opposed wing vertically, the rotated portion of the opposed wings having at least one engine;
actuating the at least one engine; and
independently controlling an output of the at least one engine to hover the aircraft.
18. The method according to claim 17 , further comprising rotating the rotated portion of the opposed wings having the at least one engine mounted thereto to orient the at least one engine and a leading edge of the wing horizontally for forward flight.
19. The method according to claim 17 , further comprising pausing rotation of the rotated portion of the opposed wings such that the opposed wings and the at least one engine are between a vertical and a horizontal orientation to transition between hovering and forward flight.
20. The method according to claim 17 , wherein independently controlling the output of the at least one engine to hover the aircraft comprises varying a pitch of a plurality of blades of a propeller coupled to the at least one engine.