Tilt-wing aircraft
In various embodiments, a tilt-wing aircraft includes a fuselage; a first wing tiltably mounted at or near a forward end of the fuselage; and a second wing rotatably mounted to the fuselage at a position aft of the first wing. A first plurality of rotors is mounted on the first wing at locations on or near a leading edge of the first wing, with two or more rotors being mounted on wing portions on each side of the fuselage; and a second plurality of rotors mounted on the second wing at locations on or near a leading edge of the second wing, with two or more rotors being mounted on wing portions on each side of the fuselage. A flight control system generates a set of actuators and associated actuator parameters to achieve desired forces and moments.
1. A tilt-wing aircraft, comprising:
a fuselage;
a first wing tiltably mounted at or near a forward end of the fuselage;
a second wing rotatably mounted to the fuselage at a position aft of the first wing;
wherein the first wing and the second wing each is coupled to the fuselage by a tilt mechanism configured to rotate a wing between a first position in which the wing is substantially in a vertical orientation with respect to the fuselage and a second position in which the wing is substantially in a horizontal orientation with respect to the fuselage;
a first plurality of rotors mounted on the first wing at locations on or near a leading edge of the first wing, with two or more rotors being mounted on wing portions on each side of the fuselage;
a second plurality of rotors mounted on the second wing at locations on or near a leading edge of the second wing, with two or more rotors being mounted on wing portions on each side of the fuselage; and
a flight control system configured to determine a set of desired forces and moments based at least in part on a set of inceptor inputs; receive sensor data; generate, based at least in part on said sensor data and said set of desired forces and moments, a set of actuators and associated actuator parameters the set of actuators being selected from a superset of actuators that includes the first plurality of rotors and the second plurality of rotors; and provide to each actuator in the generated set a corresponding set of one or more actuator parameters generated for that actuator.
2. The tilt-wing aircraft of claim 1 , wherein each of said rotors includes a housing configured to direct airflow generated by said rotor across an associated aerodynamic surface.
3. The tilt-wing aircraft of claim 2 , wherein a shape of the housing directs airflow generated by said rotor across the associated aerodynamic surface.
4. The tilt-wing aircraft of claim 3 , wherein the housing comprises an annular outlet duct configured to direct airflow generated by said rotor across the associated aerodynamic surface.
5. The tilt-wing aircraft of claim 2 , wherein the associated aerodynamic surface comprises a surface of a corresponding one of the first wing or the second wing.
6. The tilt-wing aircraft of claim 2 , wherein the associated aerodynamic surface comprises a movable aerodynamic control surface mounted on a trailing edge of a corresponding one of the first wing or the second wing.
7. The tilt-wing aircraft of claim 6 , wherein the associated aerodynamic surface comprises an aileron.
8. The tilt-wing aircraft of claim 7 , wherein the aileron is positioned on a trailing edge of said corresponding one of the first wing or the second wing at a position directly aft of a corresponding one of said rotors.
9. The tilt-wing aircraft of claim 8 , wherein the aileron has a width such that the airflow of said corresponding one of said rotors is directed to flow substantially across the aileron.
10. The tilt-wing aircraft of claim 9 , wherein the width and position are such that substantial airflow of other ones of said rotors is not directed to flow substantially across the aileron.
11. The tilt-wing aircraft of claim 1 , wherein the first wing is mounted forward of a center of gravity of the fuselage.
12. The tilt-wing aircraft of claim 1 , wherein the second wing is mounted aft of a center of gravity of the fuselage.
13. The tilt-wing aircraft of claim 1 , wherein the second wing includes on each end a vertically oriented tail portion.
14. The tilt-wing aircraft of claim 13 , further comprising a rudder positioned at a trailing edge of each tail portion.
15. The tilt-wing aircraft of claim 1 , wherein the first plurality of rotors and the second plurality of rotors are each driven by a corresponding electric motor.
16. The tilt-wing aircraft of claim 1 , wherein the superset of actuators includes one or more aerodynamic control surfaces.
17. The tilt-wing aircraft of claim 1 , wherein the first plurality of rotors and the second plurality of rotors have variable pitch rotor blades.
18. The tilt-wing aircraft of claim 17 , wherein the flight control system is further configured to vary a pitch of the first plurality of rotors and the second plurality of rotors.
19. The tilt-wing aircraft of claim 1 , wherein the first wing and the second wing are of comparable length.
20. The tilt-wing aircraft of claim 1 , wherein the first plurality of rotors and the second plurality of rotors are equal in number.