Combination flight and ground apparatus for a vehicle

Patent metadata

Field	Value
Publication number	US-11046416-B2
Application number	US-201816054307-A
Country	US
Kind code	B2
Filing date	Aug 3, 2018
Priority date	Aug 3, 2018
Publication date	Jun 29, 2021
Grant date	Jun 29, 2021

Abstract

A vehicle includes a fuselage having a longitudinal axis and a propulsion system that is coupled to the fuselage. The vehicle also includes a pair of articulated appendages that is coupled to the fuselage. Each one of the articulated appendages includes a plurality of airfoil segments and is moveable between a ground configuration, in which each one of the pair of articulated appendages supports the vehicle during takeoff or landing of the vehicle, and a flight configuration, in which each one of the pair of articulated appendages produces lift during flight of the vehicle.

First claim

What is claimed is:

1. A vehicle comprising:
a fuselage comprising a longitudinal axis;
a propulsion system coupled to the fuselage;
a pair of articulated appendages, each one of the pair of articulated appendages comprising:
an inboard end coupled to the fuselage;
an outboard end opposite the inboard end; and
a plurality of airfoil segments extending from the inboard end to the outboard end; and

a sensor located at the outboard end of each one of the pair of articulated appendages,
wherein:
each one of the pair of articulated appendages is moveable between a ground configuration, in which the outboard end of each one of the pair of articulated appendages supports the vehicle on a landing surface during takeoff or landing of the vehicle, and a flight configuration, in which each one of the pair of articulated appendages produces lift during flight of the vehicle; and
the sensor is configured to detect at least one of a location of the landing surface relative to the outboard end of a respective one of the pair of articulated appendages, motion of the landing surface relative to the outboard end of the respective one of the pair of articulated appendages, and a slope of the landing surface when the pair of articulated appendages is in the ground configuration.

2. The vehicle of claim 1 , wherein the plurality of airfoil segments of each one of the pair of articulated appendages comprises:
an inboard airfoil segment coupled to the fuselage;
an intermediate airfoil segment pivotally coupled with the inboard airfoil segment along a first pivot axis; and
an outboard airfoil segment pivotally coupled with the intermediate airfoil segment along a second pivot axis.

3. The vehicle of claim 2 , wherein the inboard airfoil segment is fixed relative to the fuselage of the vehicle.

4. The vehicle of claim 3 , wherein the intermediate airfoil segment is pivotally movable about the first pivot axis relative to the inboard airfoil segment in an upward direction and a downward direction.

5. The vehicle of claim 4 , wherein the outboard airfoil segment is pivotally movable about the second pivot axis relative to the intermediate airfoil segment in an upward direction and a downward direction.

6. The vehicle of claim 5 , wherein:
the intermediate airfoil segment comprises an intermediate spanwise axis; and
the intermediate airfoil segment is rotationally movable about the intermediate spanwise axis relative to the inboard airfoil segment.

7. The vehicle of claim 6 , wherein:
the outboard airfoil segment comprises an outboard spanwise axis; and
the outboard airfoil segment is rotationally movable about the outboard spanwise axis relative to the intermediate airfoil segment.

8. The vehicle of claim 2 , wherein the first pivot axis is parallel to the longitudinal axis of the fuselage.

9. The vehicle of claim 2 , wherein the first pivot axis is oblique to the longitudinal axis of the fuselage.

10. The vehicle of claim 2 , wherein the second pivot axis is parallel to the longitudinal axis of the fuselage.

11. The vehicle of claim 2 , wherein the second pivot axis is oblique to the longitudinal axis of the fuselage.

12. The vehicle of claim 2 , wherein the first pivot axis and the second pivot axis are parallel to each another.

13. The vehicle of claim 2 , wherein the first pivot axis and the second pivot axis are oblique to each another.

14. The vehicle of claim 1 , further comprising a controller configured to independently actuate movement of each one of the pair of articulated appendages and process a signal from the sensor.

15. The vehicle of claim 1 , wherein the sensor comprises at least one of an optical sensor and a pressure sensor.

16. The vehicle of claim 1 , wherein each one of the pair of articulated appendages further comprises:
a spanwise dimension and a chordwise dimension;
a plurality of spanwise structural components extending along the spanwise dimension;
a plurality of chordwise structural components coupled to the spanwise structural components and extending along the chordwise dimension; and
a plurality of skin panels coupled to the chordwise structural components.

17. The vehicle of claim 1 , further comprising a pair of second articulated appendages coupled to the fuselage, wherein each one of the pair of second articulated appendages comprises a plurality of second airfoil segments and is moveable between the ground configuration, in which each one of the pair of second articulated appendages supports the vehicle during takeoff or landing of the vehicle, and the flight configuration, in which each one of the pair of second articulated appendages produces lift during flight of the vehicle.

18. A combination flight and ground apparatus for a vehicle, the apparatus comprising:
an articulated appendage comprising:
an inboard end configured to be coupled to the vehicle;
an outboard end opposite the inboard end;
a plurality of airfoil segments extending from the inboard end to the outboard end; and
at least one actuator coupled to the plurality of airfoil segments and configured to move the plurality of airfoil segments between a ground configuration, in which the outboard end of the articulated appendage supports the vehicle on a landing surface during takeoff or landing of the vehicle, and a flight configuration, in which the articulated appendage produces lift during flight of the vehicle;

at least one sensor located at the outboard end of the articulated appendage and configured to detect at least one of a location of the landing surface relative to the outboard end of the articulated appendage, motion of the landing surface relative to the outboard end of the articulated appendage, and a slope of the landing surface when the articulated appendage is in the ground configuration; and
a controller coupled to the at least one actuator and to the at least one sensor, wherein the controller is configured to control movement of the plurality of airfoil segments and to process a signal from the at least one sensor.

19. A method for operating a vehicle, the method comprising:
pivotally moving at least one of a plurality of airfoil segments of each one of a pair of articulated appendages, coupled to a fuselage of the vehicle, into a flight configuration, in which each one of the pair of articulated appendages produces lift during flight of the vehicle;
pivotally moving at least one of the plurality of airfoil segments of each one of the pair of articulated appendages into a ground configuration, in which an outboard end of each one of the pair of articulated appendages supports the vehicle on a landing surface during takeoff or landing of the vehicle; and
detecting at least one of a location of the landing surface relative to the outboard end of a respective one of the pair of articulated appendages, motion of the landing surface relative to the outboard end of the respective one of the pair of articulated appendages, and a slope of the landing surface when the pair of articulated appendages is in the ground configuration.

20. The method of claim 19 , further comprising at least one of pivotally moving and rotationally moving at least one of the plurality of airfoil segments of each one of the pair of articulated appendages to control an attitude of the vehicle during flight of the vehicle.

Assignees

• Aurora Flight Sciences Corp

Inventors

• Bosworth William
• Heafitz Andrew

Classifications

• B64U60/70

  Movable wings, rotor supports or shrouds acting as ground-engaging elements · CPC title

• B64D45/04

  Landing aids; Safety measures to prevent collision with earth's surface · CPC title

• B64C2025/325

  specially adapted for helicopters · CPC title

• B64C27/22 Primary

  Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft · CPC title

• B64C3/38 Primary

  Adjustment of complete wings or parts thereof · CPC title