Aircraft having M-wing and gull wing configurations

Patent metadata

Field	Value
Publication number	US-10814973-B2
Application number	US-201815956282-A
Country	US
Kind code	B2
Filing date	Apr 18, 2018
Priority date	Apr 18, 2018
Publication date	Oct 27, 2020
Grant date	Oct 27, 2020

Abstract

An aircraft includes a fuselage coupled to a wing having a dihedral root section with first and second outboard sections pivotably coupled to respective outboard ends thereof. A thrust array is coupled to the wing. A power system is operably associated with the thrust array to provide power to each of a plurality of propulsion assemblies. A flight control system is operably associated with the thrust array and the wing. The flight control system is operable to control the thrust output from the propulsion assemblies and the configuration of the wing. In a thrust-borne vertical lift mode, the wing has an M-wing configuration with the center of gravity of the aircraft located between the outboard sections of the wing. In a wing-borne forward flight mode, the wing has a gull wing configuration with the center of gravity of the aircraft located below the outboard sections of the wing.

First claim

What is claimed is:

1. An aircraft having a thrust-borne vertical lift mode and a wing-borne forward flight mode, the aircraft comprising:
a fuselage;
a wing coupled to the fuselage, the wing having a dihedral root section with first and second outboard ends, a first outboard section pivotable relative to the first outboard end of the dihedral root section and a second outboard section pivotable relative to the second outboard end of the dihedral root section;
a thrust array including a first inboard propulsion assembly coupled between the first outboard end of the dihedral root section and the first outboard section of the wing forming a first pivot axis, a second inboard propulsion assembly coupled between the second outboard end of the dihedral root section and the second outboard section of the wing forming a second pivot axis, a first outboard propulsion assembly coupled to the first outboard section of the wing and a second outboard propulsion assembly coupled to the second outboard section of the wing;
a power system including an engine and a drive system, the drive system including first and second bevel gear sets, the first bevel gear set including an input gear configured to receive torque from the engine, a first output gear rotatable about the first pivot axis and configured to provide torque to the first inboard propulsion assembly and a second output gear configured to provide torque to the first outboard propulsion assembly, the second bevel gear set including an input gear configured to receive torque from the engine, a first output gear rotatable about the second pivot axis and configured to provide torque to the second inboard propulsion assembly and a second output gear configured to provide torque to the second outboard propulsion assembly; and
a flight control system operably associated with the thrust array and the wing, the flight control system operable to control thrust output from each of the propulsion assemblies and operable to control wing configuration;
wherein, in the thrust-borne vertical lift mode, the wing has an M-wing configuration with the center of gravity of the aircraft located between the outboard sections of the wing;
wherein, in the wing-borne forward flight mode, the wing has a gull wing configuration with the center of gravity of the aircraft located below the outboard sections of the wing; and
wherein, during transitions between the M-wing configuration and the gull wing configuration, the second output gear precesses about the first output gear changing an angle between the input gear and the second output gear, for both the first and second bevel gear sets.

2. The aircraft as recited in claim 1 wherein the propulsion assemblies further comprise variable pitch rotor blades operable to change thrust output responsive to changes in rotor blade pitch.

3. The aircraft as recited in claim 1 wherein the propulsion assemblies further comprise fixed pitch rotor blades operable to change thrust output responsive to changes in rotational speed.

4. The aircraft as recited in claim 1 wherein the engine further comprises an internal combustion engine.

5. The aircraft as recited in claim 1 wherein the power system further comprises at least one alternator driven by the engine and at least one battery charged by the at least one alternator.

6. The aircraft as recited in claim 1 wherein, in the thrust-borne vertical lift mode, the flight control system is operable to control pitch, roll and yaw responsive to differential thrust output from the propulsion assemblies of the thrust array.

7. The aircraft as recited in claim 1 wherein, in the wing-borne forward flight mode, the flight control system is operable to control yaw responsive to differential thrust output from the propulsion assemblies of the thrust array and wherein the dihedral root section has a V-shape that adds aerodynamic surface to improve yaw stability.

8. The aircraft as recited in claim 1 wherein the first outboard section of the wing further comprises a first aerosurface, wherein the second outboard section of the wing further comprises a second aerosurface and wherein, in the wing-borne forward flight mode, the flight control system is operable to control pitch and roll responsive to operation of the first and second aerosurfaces.

9. The aircraft as recited in claim 1 wherein, in the thrust-borne vertical lift mode, the outboard sections of the wing each form an acute minor angle with the dihedral root section of the wing and wherein, in the wing-borne forward flight mode, the outboard sections of the wing each form an obtuse minor angle with the dihedral root section of the wing.

10. The aircraft as recited in claim 1 wherein, during transitions from the thrust-borne vertical lift mode to the wing-borne forward flight mode, the wing transitions from the M-wing configuration to the gull wing configuration.

11. The aircraft as recited in claim 1 wherein, after transitions from the thrust-borne vertical lift mode to the wing-borne forward flight mode, the wing transitions from the M-wing configuration to the gull wing configuration.

12. The aircraft as recited in claim 1 wherein, during transitions from the wing-borne forward flight mode to the thrust-borne vertical lift mode, the wing transitions from the gull wing configuration to the M-wing configuration.

13. The aircraft as recited in claim 1 wherein the flight control system further comprises a remote controlled flight control system.

14. The aircraft as recited in claim 1 wherein the flight control system further comprises an autonomous flight control system.

15. A multi-aircraft system including at least first and second aircraft connectable wingtip-to-wingtip during flight, each aircraft having a thrust-borne vertical lift mode and a wing-borne forward flight mode and each aircraft comprising:
a fuselage;
a wing coupled to the fuselage, the wing having a dihedral root section with first and second outboard ends, a first outboard section pivotable relative to the first outboard end of the dihedral root section and a second outboard section pivotable relative to the second outboard end of the dihedral root section;
a thrust array including a first inboard propulsion assembly coupled between the first outboard end of the dihedral root section and the first outboard section of the wing forming a first pivot axis, a second inboard propulsion assembly coupled between the second outboard end of the dihedral root section and the second outboard section of the wing forming a second pivot axis, a first outboard propulsion assembly coupled to the first outboard section of the wing and a second outboard propulsion assembly coupled to the second outboard section of the wing;
a power system including an engine and a drive system, the drive system including first and second bevel gear sets, the first bevel gear set including an input gear configured to receive torque from the engine, a first output gear rotatable about the first pivot axis and configured to provide torque to the first inboard propulsion assembly and a second output gear configured to provide torque to the first outboard propulsion assembly, the second bevel gear set including an input gear configured to receive torque from the engine, a first output gear rotatable about the second pivot axis and configured to provide torque to the second inboard propulsion assembly and a second output gear configured to provide torque to the second outboard propulsion assembly; and
a female wingtip coupling assembly at the outboard end of the first outboard section;
a male wingtip coupling assembly at the outboard en

Assignees

• Textron Innovations Inc

Inventors

• Gaffney Sean Robert
• Graham Jr Robert Rex
• Campbell Colton Edward
• Prasadk Kevin Krisnil
• Martinez Isaiah Neves
• Rosenkrance Jared Michael
• Everhart Lukas N
• Crisler William Paul

Classifications

• B64U2201/10

  autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS] · CPC title

• B64U2201/20

  Remote controls · CPC title

• B64U50/19

  using electrically powered motors · CPC title

• B64U10/20

  Vertical take-off and landing [VTOL] aircraft (flying platforms B64U10/13; helicopters B64U10/17) · CPC title

• B64U50/11

  using internal combustion piston engines · CPC title