Aircraft having hover stability in inclined flight attitudes

Patent metadata

Field	Value
Publication number	US-10633087-B2
Application number	US-201816154250-A
Country	US
Kind code	B2
Filing date	Oct 8, 2018
Priority date	Jul 1, 2016
Publication date	Apr 28, 2020
Grant date	Apr 28, 2020

Abstract

An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes an airframe having first and second wings with first and second pylons coupled therebetween. The airframe has a longitudinal axis and a lateral axis in hover. A two-dimensional distributed thrust array is coupled to the airframe. The thrust array includes a plurality of propulsion assemblies each operable for variable speed and omnidirectional thrust vectoring. A flight control system is operable to independently control the speed and thrust vector of each of the propulsion assemblies such that in an inclined flight attitude with at least one of the longitudinal axis and the lateral axis extending out of a horizontal plane, the flight control system is operable to maintain hover stability responsive to controlling the speed and the thrust vector of the propulsion assemblies.

First claim

What is claimed is:

1. An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation, the aircraft comprising:
an airframe including first and second wings with first and second pylons coupled therebetween, the airframe having a longitudinal axis and a lateral axis in hover;
a two-dimensional distributed thrust array coupled to the airframe, the thrust array including a plurality of propulsion assemblies each operable for variable speed; and
a flight control system operable to independently control the speed of each of the propulsion assemblies;
wherein, the flight control system is configured such that, in an inclined flight attitude with at least one of the longitudinal axis and the lateral axis extending out of a horizontal plane, the flight control system is operable to maintain hover stability responsive to controlling the speed of each of the propulsion assemblies.

2. The aircraft as recited in claim 1 wherein each of the propulsion assemblies further comprises an electric motor, a rotor assembly coupled to the electric motor, a speed controller coupled between the flight control system and the electric motor and a two-axis gimbal coupled to the electric motor operable to tilt the electric motor and the rotor assembly relative to the airframe to provide omnidirectional thrust vectoring; and
wherein, the flight control system is operable to maintain the hover stability responsive to controlling the speed and the thrust vector of each of the propulsion assemblies.

3. The aircraft as recited in claim 1 wherein the first and second wings each have first and second nacelle stations and wherein the two-dimensional distributed thrust array further comprises two propulsion assemblies coupled to the first and second nacelle stations of the first wing and two propulsion assemblies coupled to the first and second nacelle stations of the second wing.

4. The aircraft as recited in claim 1 wherein the inclined flight attitude with at least one of the longitudinal axis and the lateral axis extending out of the horizontal plane further comprises a nonzero pitch flight attitude.

5. The aircraft as recited in claim 1 wherein the inclined flight attitude with at least one of the longitudinal axis and the lateral axis extending out of the horizontal plane further comprises a pitch down flight attitude.

6. The aircraft as recited in claim 1 wherein the inclined flight attitude with at least one of the longitudinal axis and the lateral axis extending out of the horizontal plane further comprises a pitch up flight attitude.

7. The aircraft as recited in claim 1 wherein the inclined flight attitude with at least one of the longitudinal axis and the lateral axis extending out of the horizontal plane further comprises a nonzero roll flight attitude.

8. The aircraft as recited in claim 1 wherein the inclined flight attitude with at least one of the longitudinal axis and the lateral axis extending out of the horizontal plane further comprises a roll left flight attitude.

9. The aircraft as recited in claim 1 wherein the inclined flight attitude with at least one of the longitudinal axis and the lateral axis extending out of the horizontal plane further comprises a roll right flight attitude.

10. The aircraft as recited in claim 1 wherein the inclined flight attitude with at least one of the longitudinal axis and the lateral axis extending out of the horizontal plane further comprises an incline angle of between about five degrees and about fifteen degrees.

11. The aircraft as recited in claim 1 wherein the inclined flight attitude with at least one of the longitudinal axis and the lateral axis extending out of the horizontal plane further comprises an incline angle of between about fifteen degrees and about twenty-five degrees.

12. The aircraft as recited in claim 1 further comprising a payload coupled to the airframe.

13. The aircraft as recited in claim 12 wherein the payload is selected from the group consisting of a package delivery module, an air reconnaissance module, a light detection and ranging module, a camera module, an optical targeting module, a laser module, a sensors module, an air-to-ground weapons module, an air-to-air weapons module, a communications module and a cargo hook module.

14. The aircraft as recited in claim 1 further comprising a plurality of aerosurfaces operably associated with the airframe and wherein, in the inclined flight attitude with at least one of the longitudinal axis and the lateral axis extending out of the horizontal plane, the flight control system is operable to maintain the hover stability responsive to controlling the speed of each of the propulsion assemblies and the position of each of the aerosurfaces.

15. The aircraft as recited in claim 14 wherein each of the propulsion assemblies further comprises a nacelle and wherein each of the aerosurfaces is rotatably coupled to one of the nacelles.

16. The aircraft as recited in claim 1 wherein the hover stability in the inclined flight attitude enables vertical takeoffs and landings relative to unlevel surfaces.

17. The aircraft as recited in claim 1 wherein the hover stability in the inclined flight attitude enables payload orientation relative to a ground object.

18. The aircraft as recited in claim 1 wherein the hover stability in the inclined flight attitude enables self-docking.

19. An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation, the aircraft comprising:
an airframe including first and second wings with first and second pylons coupled therebetween, the airframe having a longitudinal axis and a lateral axis in hover;
a two-dimensional distributed thrust array coupled to the airframe, the thrust array including a plurality of propulsion assemblies each operable for variable speed;
a flight control system operable to independently control the speed of each of the propulsion assemblies; and
a payload coupled to the airframe;
wherein, the flight control system is configured such that, in an inclined flight attitude with at least one of the longitudinal axis and the lateral axis extending out of a horizontal plane, the flight control system is operable to maintain hover stability responsive to controlling the speed of each of the propulsion assemblies, thereby enabling payload orientation relative to a ground object.

20. An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation, the aircraft comprising:
an airframe including first and second wings with first and second pylons coupled therebetween, the airframe having a longitudinal axis and a lateral axis in hover;
a two-dimensional distributed thrust array coupled to the airframe, the thrust array including a plurality of propulsion assemblies each operable for variable speed;
a flight control system operable to independently control the speed of each of the propulsion assemblies; and
a payload coupled to the airframe, the payload including a package delivery module;
wherein, the flight control system is configured such that, in an inclined flight attitude with at least one of the longitudinal axis and the lateral axis extending out of a horizontal plane, the flight control system is operable to maintain hover stability responsive to controlling the speed of each of the propulsion assemblies, thereby enabling self-docking for package pickup and drop-off.

Assignees

• Textron Innovations Inc

Inventors

• Mccullough John Richard
• Oldroyd Paul K

Classifications

• B64C29/02

  having its flight directional axis vertical when grounded · CPC title

• B64C39/08 Primary

  having multiple wings · CPC title

• B64C2211/00

  Modular constructions of airplanes or helicopters · CPC title

• B64C29/0025 Primary

  the propellers being fixed relative to the fuselage · CPC title

• B64C2201/141

  Operations & Transport · mapped topic