Unmanned aerial vehicles with compact storage mode

Patent metadata

Field	Value
Publication number	US-10894602-B2
Application number	US-201816113519-A
Country	US
Kind code	B2
Filing date	Aug 27, 2018
Priority date	Aug 27, 2018
Publication date	Jan 19, 2021
Grant date	Jan 19, 2021

Abstract

An unmanned aerial vehicle has a flight mode and a compact storage mode. The unmanned aerial vehicle includes an airframe having first and second wings with first and second pylons extending therebetween. A thrust array is coupled to the airframe including two propulsion assemblies coupled to each of the first and second wings. An electric power system is operably associated with the thrust array and operable to provide power to each propulsion assembly. A flight control system is operably associated with the thrust array and operable to independently control the speed of each propulsion assembly. In the flight mode, the first and second wings are substantially parallel with the vertical dimension therebetween at a maximum. In the compact storage mode, the first and second pylons are rotated relative to the first and second wings such that the vertical dimension between the first and second wings is at a minimum.

First claim

What is claimed is:

1. An unmanned aerial vehicle having a flight mode and a compact storage mode, the unmanned aerial vehicle comprising:
an airframe including a first wing having an airfoil cross section and a planar lower surface defining a first principal plane, a second wing having an airfoil cross section and a planar lower surface defining a second principal plane and first and second pylons extending between and pivotably coupled to the lower surface of the first wing and an upper surface of the second wing;
a thrust array coupled to the airframe including first and second propulsion assemblies coupled to the first wing and third and fourth propulsion assemblies coupled to the second wing;
an electric power system operably associated with the thrust array and operable to provide power to each propulsion assembly; and
a flight control system operably associated with the thrust array and operable to independently control the speed of each propulsion assembly;
wherein, in the flight mode, the first principal plane is parallel with the second principal plane and the first pylon is parallel with the second pylon such that the airframe has a rectangular cross section with a vertical dimension between the first and second wings at a maximum; and
wherein, in the compact storage mode, the first and second pylons are rotated relative to the first and second wings such that the first principal plane is parallel with the second principal plane and the first pylon is parallel with the second pylon such that the airframe has a parallelogram shaped cross section with the vertical dimension between the first and second wings at a minimum.

2. The unmanned aerial vehicle as recited in claim 1 wherein the first and second pylons are respectively coupled to the first and second wings at pivot joints.

3. The unmanned aerial vehicle as recited in claim 1 wherein the first and second pylons are lockable relative to the first wing in the flight mode and in the compact storage mode to prevent relative rotation therebetween.

4. The unmanned aerial vehicle as recited in claim 1 further comprising a first pivot lock coupling the first pylon to the first wing and a second pivot lock coupling the second pylon to the first wing.

5. The unmanned aerial vehicle as recited in claim 4 wherein the first and second pivot locks each have a locked configuration in which the first and second pivot locks respectively prevent relative rotation between the first and second pylons and the first wing in the flight mode and in the compact storage mode.

6. The unmanned aerial vehicle as recited in claim 4 wherein the first and second pivot locks each have an actuated configuration in which the first and second pivot locks respectively allow relative rotation between the first and second pylons and the first wing such that the airframe is operable to articulate between the flight mode and the compact storage mode.

7. The unmanned aerial vehicle as recited in 1 wherein the first and second wings shift laterally and move vertically relative to each other when the airframe articulates between the flight mode and the compact storage mode.

8. The unmanned aerial vehicle as recited in 1 wherein the first and second wings shift fore-aft and move vertically relative to each other when the airframe articulates between the flight mode and the compact storage mode.

9. The unmanned aerial vehicle as recited in 1 wherein the first and second wings move vertically relative to each other when the airframe articulates between the flight mode and the compact storage mode.

10. The unmanned aerial vehicle as recited in claim 1 further comprising third and fourth pylons extending between and pivotably coupled to the lower surface of the first wing and the upper surface of the second wing.

11. The unmanned aerial vehicle as recited in claim 10 wherein each of the pylons has a hinge joint operable to extend in the outboard direction as the airframe articulates from the flight mode and the compact storage mode and reduces the vertical dimension between the first and second wings.

12. The unmanned aerial vehicle as recited in claim 10 wherein each of the pylons has a hinge joint operable to extend in the inboard direction as the airframe articulates from the flight mode and the compact storage mode and reduces the vertical dimension between the first and second wings.

13. The unmanned aerial vehicle as recited in claim 1 wherein each propulsion assembly comprises an electric motor and a rotor assembly.

14. The unmanned aerial vehicle as recited in claim 1 wherein the first and second propulsion assemblies are positioned on a leading edge of the first wing and the third and fourth propulsion assemblies are positioned on a leading edge of the second wing in the flight mode.

15. The unmanned aerial vehicle as recited in claim 1 wherein the electric power system comprises one or more batteries and at least one power controller.

16. The unmanned aerial vehicle as recited in claim 1 wherein the flight control system is operable for autonomous flight control of the unmanned aerial vehicle.

17. The unmanned aerial vehicle as recited in claim 1 wherein the flight control system is operable to communicate with a remote station.

18. The unmanned aerial vehicle as recited in claim 1 further comprising a plurality of electronic speed controllers, each operably associated with one of the propulsion assemblies.

19. An unmanned aerial vehicle having a flight mode and a compact storage mode, the unmanned aerial vehicle comprising:
an airframe including first and second wings each having an airfoil cross section and a planar lower surface defining first and second principal planes and first and second pylons extending between and pivotably coupled to the lower surface of the first wing and an upper surface of the second wing;
a thrust array coupled to the airframe including first and second propulsion assemblies coupled to the first wing and third and fourth propulsion assemblies coupled to the second wing;
an electric power system operably associated with the thrust array and operable to provide power to each propulsion assembly; and
a flight control system operably associated with the thrust array and operable to independently control the speed of each propulsion assembly;
wherein, in the flight mode, the first principal plane is parallel with the second principal plane and the first pylon is parallel with the second pylon such that the airframe has a rectangular cross section with a vertical dimension between the first and second wings at a maximum;
wherein, in the compact storage mode, the first and second pylons are rotated relative to the first and second wings such that the first principal plane is parallel with the second principal plane and the first pylon is parallel with the second pylon such that the airframe has a parallelogram shaped cross section with the vertical dimension between the first and second wings at a minimum; and
wherein, the first and second pylons are lockable relative to the first wing in the flight mode and in the compact storage mode to prevent relative rotation therebetween.

Assignees

• Textron Innovations Inc

Inventors

• Hefner Levi Charles
• Easley Dakota Charles

Classifications

• B64U50/19 Primary

  using electrically powered motors · CPC title

• B64U10/70

  Convertible aircraft, e.g. convertible into land vehicles · CPC title

• B64U30/20

  Rotors; Rotor supports · CPC title

• B64U30/12

  Variable or detachable wings, e.g. wings with adjustable sweep · CPC title

• B64C2211/00

  Modular constructions of airplanes or helicopters · CPC title