Unmanned aerial vehicle with monolithic wing and twin-rotor propulsion/lift modules

Patent metadata

Field	Value
Publication number	US-10850835-B2
Application number	US-201715474014-A
Country	US
Kind code	B2
Filing date	Mar 30, 2017
Priority date	Mar 30, 2017
Publication date	Dec 1, 2020
Grant date	Dec 1, 2020

Abstract

Various embodiments include a drone capable of operating as an airplane, a quad-copter, or a hybrid aircraft using a versatile flight performance envelope enabled by six elements of control. The drone may include a monolithic wing with a propulsion/lift module connected to each wing tip. Each propulsion/lift module may include a pivotal support structure configured to pivot around a longitudinal axis of the monolithic wing, with two pylons extending radially outwardly from the pivotal support structure and at least partially away from one another, and a propulsion units positioned on a distal end of each pylon. The pivotal support structures may be coupled to the monolithic wing via a servo motor enabling a processor to individually control rotation of each propulsion/lift module to provide roll and pitch control. Thrust and rotation of the propulsion units may be individually controlled by the processor to provide yaw, roll and pitch control.

First claim

What is claimed is:

1. An aerial drone, comprising:
a monolithic wing having two wing tips; and
two propulsion/lift modules, wherein a first one of the two propulsion/lift modules is connected to a first one of the two wing tips by a first servo motor and a second one of the two propulsion/lift modules is connected to a second one of the two wing tips by a second servo motor, and wherein each of the two propulsion/lift modules comprises:
a pivotal support structure configured to pivot around a longitudinal axis extending laterally across the monolithic wing;
two pylons extending radially outwardly from the pivotal support structure and at least partially away from one another; and
two propulsion units with one propulsion unit attached to a distal end of each pylon,

wherein when the aerial drone is in a vertical takeoff and landing (VTOL) flight mode, the two propulsion/lift modules are rotated with respect to the monolithic wing so that thrust from the two propulsion/lift modules is directed approximately perpendicular to a lifting surface of the monolithic wing.

2. The aerial drone of claim 1 , wherein the two pylons extending radially outwardly from the pivotal support structure comprise two pylons extending obliquely outward from each wing tip.

3. The aerial drone of claim 1 , wherein the two propulsion/lift modules are further configured to rotate with respect to the monolithic wing to enable the aerial drone to operate in a flat-spin flight mode and in a wing flight mode.

4. The aerial drone of claim 1 , wherein the pivotal support structure includes a trailing edge, and wherein when the aerial drone is in the VTOL flight mode, the trailing edges of the pivotal support structure are positioned to provide a landing structure.

5. The aerial drone of claim 1 , wherein during a transition to or from the VTOL flight mode, the two propulsion/lift modules rotate through approximately 90 degrees, and wherein the monolithic wing is configured so that rotors of the two propulsion units do not strike the monolithic wing.

6. The aerial drone of claim 3 , wherein when the aerial drone is in the wing flight mode, the two propulsion/lift modules are rotated with respect to the monolithic wing so that thrust from the two propulsion/lift modules is directed approximately parallel to the lifting surface of the monolithic wing.

7. The aerial drone of claim 3 , wherein when the aerial drone is in the flat-spin flight mode, the two propulsion/lift modules are rotated independently with respect to the monolithic wing into positions at which rotors generate yaw forces.

8. The aerial drone of claim 1 , further comprising:
a processor, coupled to the first servo motor and the second servo motor, located in the monolithic wing.

9. The aerial drone of claim 1 , further comprising an empennage connected to the monolithic wing.

10. The aerial drone of claim 1 , wherein the monolithic wing is modular and replaceable with another monolithic wing having a different flight characteristic.

11. The aerial drone of claim 1 , wherein the monolithic wing includes a cargo volume for holding a payload.

12. A propulsion/lift module, comprising:
a pivotal support structure coupled to a wing tip of a monolithic wing by a servo motor and configured to rotate relative to the monolithic wing;
two pylons extending radially from two surfaces of the pivotal support structure, wherein each of the two pylons project obliquely outward from the wing tip; and
two propulsion units, wherein one of the two propulsion units is mounted to a distal end of each pylon,
wherein in a vertical takeoff and landing (VTOL) flight mode, the propulsion/lift module is rotated with respect to the monolithic wing so that thrust from the propulsion/lift module is directed approximately perpendicular to a lifting surface of the monolithic wing.

13. The propulsion/lift module of claim 12 , further comprising two rotors, wherein one rotor is coupled to each propulsion unit.

14. A method of operating an unmanned aerial vehicle (drone) comprising a monolithic wing having two wing tips and two propulsion/lift modules, wherein each of the two propulsion/lift modules comprises: a pivotal support structure configured to pivot around a longitudinal axis extending laterally across the monolithic wing, two pylons extending from the pivotal support structure and at least partially away from one another, and two propulsion units, wherein one propulsion unit is mounted to a distal end of each pylon, and wherein each pylon extends radially from a surface of the pivotal support structure and extends obliquely outward from each wing tip, the method comprising:
rotating each of the two propulsion/lift modules independently, wherein a first one of the two propulsion/lift modules is connected to a first one of the two wing tips by a first servo motor and a second one of the two propulsion/lift modules is connected to a second one of the two wing tips by a second servo motor, and wherein rotating each of the two propulsion/lift modules independently comprises rotating each pivotal support structure so that thrust from the two propulsion/lift modules is directed approximately perpendicular to a lifting surface of the monolithic wing to place the drone in a vertical takeoff and landing (VTOL) flight mode; and
controlling applied power independently to the propulsion units according to a flight mode.

15. The method of claim 14 , wherein rotating each of the two propulsion/lift modules independently further comprises rotating the two propulsion/lift modules independently with respect to the monolithic wing to enable the drone to operate in a flat-spin flight mode and in a wing flight mode.

16. The method of claim 14 , wherein rotating each of the two propulsion/lift modules independently further comprises transitioning to or from the VTOL flight mode to a wing flight mode by incrementally rotating each pivotal support structure through approximately 90 degrees.

17. The method of claim 15 , wherein rotating each of the two propulsion/lift modules independently further comprises operating the drone in the wing flight mode by rotating each pivotal support structure so that thrust from the two propulsion/lift modules is directed approximately parallel to the lifting surface of the monolithic wing.

18. The method of claim 15 , wherein rotating each of the two propulsion/lift modules independently further comprises putting the drone into the flat-spin flight mode by independently rotating the two propulsion/lift modules into positions at which rotors generate yaw forces.

19. The method of claim 14 , wherein rotating each of the two propulsion/lift modules independently and controlling the applied power independently to the propulsion units according to a flight mode comprise controlling yaw, pitch, and roll of the drone by individually controlling a rotation angle of each of the two propulsion/lift modules, and individually controlling power applied to each of the propulsion units.

20. The method of claim 19 , further comprising controlling yaw and pitch attitude by:
increasing power to the propulsion units located on a first one of the two wing tips for yaw control; and
increasing power simultaneously to either the top or bottom propulsion units at the two wing tips for pitch control.

21. The method of claim 19 , wherein rotating each of the two propulsion/lift module independently comprises controlling roll attitude by:
rotating the two propulsion/lift modules by equal but opposite ang

Assignees

• Qualcomm Inc

Inventors

• Hutson Donald

Classifications

• B64U30/10

  Wings · CPC title

• B64U2101/60

  for transporting passengers; for transporting goods other than weapons · CPC title

• B64U30/20

  Rotors; Rotor supports · CPC title

• B64U2201/20

  Remote controls · CPC title

• B64U30/40

  Empennages, e.g. V-tails (foldable or collapsible UAVs B64U20/50) · CPC title