Dual tiltwing aircraft having a quadrilateral linkage
An aircraft having a vertical takeoff and landing flight mode and a forward flight mode. The aircraft includes a fuselage and a dual tiltwing assembly having a vertical lift orientation and a forward thrust orientation relative to the fuselage. The dual tiltwing assembly includes a forward wing and an aft wing coupled together and to the fuselage by a quadrilateral linkage. A distributed propulsion system is coupled to the dual tiltwing assembly and includes a plurality of forward propulsion assemblies coupled to the forward wing and a plurality of aft propulsion assemblies coupled to the aft wing. A flight control system is operably associated with the distributed propulsion system and the dual tiltwing assembly. The flight control system is operable to independently control each of the propulsion assemblies and is operable to transition the dual tiltwing assembly between the vertical lift orientation and the forward thrust orientation.
1. An aircraft having a vertical takeoff and landing flight mode and a forward flight mode, the aircraft comprising:
a fuselage;
a dual tiltwing assembly having a vertical lift orientation and a forward thrust orientation relative to the fuselage, the dual tiltwing assembly including a forward wing, an aft wing and a quadrilateral linkage, the quadrilateral linkage coupling the forward wing to the aft wing and the quadrilateral linkage coupling the forward and aft wings to the fuselage;
a distributed propulsion system coupled to the dual tiltwing assembly, the distributed propulsion system including a plurality of forward propulsion assemblies coupled to the forward wing and a plurality of aft propulsion assemblies coupled to the aft wing; and
a flight control system operably associated with the distributed propulsion system and the dual tiltwing assembly, the flight control system operable to independently control each of the propulsion assemblies and operable to transition the dual tiltwing assembly between the vertical lift orientation and the forward thrust orientation;
wherein the quadrilateral linkage includes a fixed link formed by the fuselage, an input link coupled between the fixed link and one of the forward and aft wings, a floating link coupled between the forward wing and the aft wing and an output link coupled between the fixed link and the other of the forward and aft wings.
2. The aircraft as recited in claim 1 wherein propwash generated by the forward propulsion assemblies travels substantially in the chordwise direction of the forward wing and propwash generated by the aft propulsion assemblies travels substantially in the chordwise direction of the aft wing in both the vertical lift orientation and the forward thrust orientation of the dual tiltwing assembly.
3. The aircraft as recited in claim 1 wherein the forward wing maintains a substantially congruent angle of incidence with the aft wing during transitions between the vertical lift orientation and the forward thrust orientation of the dual tiltwing assembly.
4. The aircraft as recited in claim 1 further comprising a synchronizing link coupled between the forward wing and the aft wing to maintain an angle of incidence of the forward wing substantially congruent with an angle of incidence of the aft wing during transitions between the vertical lift orientation and the forward thrust orientation of the dual tiltwing assembly.
5. The aircraft as recited in claim 1 further comprising a rotary actuator operably disposed between the flight control system and the input link and operable to transition the dual tiltwing assembly between the vertical lift orientation and the forward thrust orientation.
6. The aircraft as recited in claim 1 wherein the quadrilateral linkage further comprises a planar quadrilateral linkage.
7. The aircraft as recited in claim 1 wherein the quadrilateral linkage further comprises a convex quadrilateral linkage.
8. The aircraft as recited in claim 1 wherein the quadrilateral linkage further comprises a non-Grashof quadrilateral linkage.
9. The aircraft as recited in claim 1 wherein each of the propulsion assemblies further comprises:
a nacelle operable to be coupled to one of the forward and aft wings;
an electric motor disposed within the nacelle;
a rotor hub mechanically coupled to the electric motor and operable to rotate responsive to operation of the electric motor; and
a proprotor mechanically coupled to the rotor hub and operable to rotate therewith.
10. The aircraft as recited in claim 1 further comprising an electrical energy source disposed within the fuselage operable to provide electrical energy to each of the propulsion assemblies.
11. The aircraft as recited in claim 1 further comprising an electrical energy generation system disposed within the fuselage operable to provide electrical energy to each of the propulsion assemblies, the electrical energy generation system including at least one internal combustion engine and an electric generator.
12. The aircraft as recited in claim 1 wherein the flight control system commands operation of the propulsion assemblies and the dual tiltwing assembly responsive to at least one of onboard pilot flight control, remote flight control, autonomous flight control and combinations thereof.
13. The aircraft as recited in claim 1 wherein the
input link comprises first and second input links coupled between the fixed link and one of the forward and aft wings;
wherein the floating link comprises first and second floating links coupled between the forward wing and the aft wing; and
wherein the output link comprises first and second output links coupled between the fixed link and the other of the forward and aft wings.
14. The aircraft as recited in claim 13 further comprising first and second synchronizing links coupled between the forward wing and the aft wing to maintain an angle of incidence of the forward wing substantially congruent with an angle of incidence of the aft wing during transitions between the vertical lift orientation and the forward thrust orientation of the dual tiltwing assembly.
15. An aircraft having a vertical takeoff and landing flight mode and a forward flight mode, the aircraft comprising:
a fuselage;
a dual tiltwing assembly having a vertical lift orientation and a forward thrust orientation relative to the fuselage, the dual tiltwing assembly including a forward wing, an aft wing and a quadrilateral linkage, the quadrilateral linkage coupling the forward wing to the aft wing and the quadrilateral linkage coupling the forward and aft wings to the fuselage;
a distributed propulsion system coupled to the dual tiltwing assembly, the distributed propulsion system including a plurality of forward propulsion assemblies coupled to the forward wing and a plurality of aft propulsion assemblies coupled to the aft wing; and
a flight control system operably associated with the distributed propulsion system and the dual tiltwing assembly, the flight control system operable to independently control each of the propulsion assemblies and operable to transition the dual tiltwing assembly between the vertical lift orientation and the forward thrust orientation;
wherein the quadrilateral linkage includes a fixed link formed by the fuselage, an input link coupled between the fixed link and one of the forward and aft wings, a floating link and a synchronizing link coupled between the forward wing and the aft wing and an output link coupled between the fixed link and the other of the forward and aft wings; and
wherein the synchronizing link maintains an angle of incidence of the forward wing substantially congruent with an angle of incidence of the aft wing during transitions between the vertical lift orientation and the forward thrust orientation of the dual tiltwing assembly.
16. The aircraft as recited in claim 15 further comprising a rotary actuator operably disposed between the flight control system and the input link and operable to transition the dual tiltwing assembly between the vertical lift orientation and the forward thrust orientation.
17. The aircraft as recited in claim 15 wherein each of the propulsion assemblies further comprises:
a nacelle operable to be coupled to one of the forward and aft wings;
an electric motor disposed within the nacelle;
a rotor hub mechanically coupled to the electric motor and operable to rotate responsive to operation of the electric motor; and
a proprotor mechanically coupled to the rotor hub and operable to rotate therewith.
18. The aircraft as recited in claim 15 further comprising an electrical energy generation system disposed within the fuselage operable to provide electrical energy to each of the propulsion assemblies, the electrical energy generation system including at least one internal combustion engine and an electric generator.
19. The aircraft as recited in claim 15 wherein the flight control system commands operation of the propulsion assemblies responsive to at least one of onboard pilot flight control, remote flight control, autonomous flight control and combinations thereof.