Vertical takeoff and landing airframe
Airframes configured for stable in-flight transition between forward flight and vertical takeoff and landing are described herein. In one embodiment, an aircraft can include a fuselage, opposed wings extending from opposed sides of the fuselage, and a plurality of engines. At least one engine can be mounted to each of the opposed wings and at least a portion of each opposed wing including at least one of the plurality of engines can rotate relative to the fuselage around a rotation axis that is non-perpendicular and transverse to a longitudinal axis of the fuselage. Rotating portions of the wings including at least one of the plurality of engines in the described manner can provide a stable and smooth transition between vertical and forward flight.
1. An aircraft, comprising:
a fuselage;
opposed wings extending from opposed sides of the fuselage;
a plurality of engines, wherein at least one engine is mounted to each of the opposed wings;
wherein at least a portion of each opposed wing including at least one of the plurality of engines rotates relative to the fuselage around a rotation axis that is non-perpendicular and transverse 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,
wherein the plurality of engines provide lift to the aircraft in the first configuration.
2. The aircraft of claim 1 , wherein a first angle between the rotation axis and the longitudinal axis of the fuselage projected in a plane containing the longitudinal axis of the fuselage and an axis extending between ends of the opposed wings is between about 35° and about 55°.
3. The aircraft of claim 2 , wherein the first angle is about 45°.
4. The aircraft of claim 2 , wherein a second angle between the rotation axis and the axis extending between ends of the opposed wings projected in a plane containing the axis extending between ends of the opposed wings and perpendicular to the longitudinal axis of the fuselage is between about 35° and about 55°.
5. The aircraft of claim 4 , wherein the second angle is about 45°.
6. The aircraft of claim 1 , wherein the plurality of engines includes at least 4 engines and each portion of the opposed wings that rotates relative to the fuselage includes at least two engines mounted thereto.
7. The aircraft of claim 1 , wherein each of the plurality of engines is an electric engine.
8. The aircraft of claim 7 , further comprising a plurality of batteries, wherein each battery is mounted to one of the opposed wings adjacent to one of the plurality of engines.
9. The aircraft of claim 1 , wherein each of the plurality of engines is any of a turbine and an internal combustion engine.
10. The aircraft of 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.
11. The aircraft of claim 10 , wherein an outboard end of each fixed portion is oblique to the longitudinal axis of the fuselage.
12. The aircraft of claim 10 , wherein, in the first configuration, an axis between a leading edge and a trailing edge of the wing is parallel to the longitudinal axis of the fuselage, and in the second configuration, the axis between the leading edge and the trailing edge of the wing is perpendicular to the longitudinal axis of the fuselage.
13. The aircraft of claim 12 , wherein the leading edge of each rotating portion of the opposed wings faces upward when the wings are in the second configuration.
14. The aircraft of claim 12 , wherein each of the plurality of engines is offset from the wing it is mounted to such that, when each wing is in the first configuration, the at least one engine mounted thereto is disposed between the wing and the fuselage.
15. The aircraft of claim 10 , wherein, in the first configuration, an axis extending between an inboard end to an outboard end of the rotating portion is perpendicular to the longitudinal axis of the fuselage, and in the second configuration, the axis extending between the inboard end and the outboard end of the rotating portion is parallel to the longitudinal axis of the fuselage.
16. The aircraft of claim 15 , wherein the leading edge of each rotating portion of the opposed wings faces upward when the wings are in the second configuration.
17. The aircraft of claim 10 , further comprising at least one landing support coupled to a trailing portion of each rotating portion of the opposed wings.
18. The aircraft of claim 17 , wherein the landing support is any of a wheel, a float, and a leg.
19. The aircraft of claim 17 , wherein the landing support is a wheel coupled to one of the engines such that the engine can rotate the wheel.
20. The aircraft of claim 10 , wherein the fixed portion and the rotating portion of each of the opposed wings are coupled by a pivot joint.
21. The aircraft of claim 20 , wherein the pivot joint is disposed in a leading portion of each opposed wing.
22. The aircraft of claim 10 , wherein each of the opposed wings further comprises an actuator to control rotation of the rotating portion relative to the fixed portion.
23. The aircraft of claim 22 , wherein the actuator includes a lead screw coupled to the rotating portion by a linkage.
24. The aircraft of claim 1 , wherein the opposed wings have an airfoil shape.
25. An aircraft, comprising:
a fuselage;
opposed wings extending from opposed sides of the fuselage;
a plurality of engines, wherein at least one engine is mounted to each of the opposed wings;
wherein at least a portion of each opposed wing including at least one of the plurality of engines rotates relative to the fuselage around a rotation axis that is non-perpendicular and transverse 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 the wings do not produce lift in the first configuration.
26. A vertical take-off or landing method, comprising: rotating at least a portion of a wing having an engine mounted thereto relative to a fuselage around a rotation axis that is non-perpendicular and transverse to a longitudinal axis of the fuselage to orient the engine and a leading edge of the wing vertically for hovering;
actuating the engine to produce vertical lift; and
rotating the at least portion of the wing having the engine mounted thereto to orient the engine and a leading edge of the wing horizontally for forward flight.
27. The method of claim 26 , wherein a leading edge of the wing faces upward when the wing is oriented vertically.
28. The method of claim 26 , wherein rotating the at least portion of the wing to orient the engine and the leading edge of the wing vertically includes pivoting the at least portion of the wing about a pivot joint disposed in a leading portion of the wing.
29. The method of claim 26 , wherein rotating the at least portion of the wing to orient the engine and the leading edge of the wing vertically includes any of hydraulically and electrically actuating such rotation.
30. The method of claim 26 , further comprising pausing rotation of the at least portion of the wing such that the wing and the engine are between a vertical and a horizontal orientation to transition between hovering and forward flight.