Wing-twist controlled aircraft

Patent metadata

Field	Value
Publication number	US-11008087-B2
Application number	US-201715702441-A
Country	US
Kind code	B2
Filing date	Sep 12, 2017
Priority date	Sep 12, 2017
Publication date	May 18, 2021
Grant date	May 18, 2021

Abstract

The present disclosure directed to an aircraft comprising one or more propulsion devices, a flexible wing, at least two tail booms having a proximal end and a distal end, the tail booms being secured to said flexible wing at the proximal end, wherein the tail booms comprise of a tail section connected at the distal end of said tail boom and wherein the tail section comprises of at least one control surface.

First claim

What is claimed is:

1. A wing-twist aircraft comprising:
a propulsion device;
a flexible wing having a first wing tip, a second wing tip, and a midpoint along its wingspan that is located substantially at the center between the first wing tip and the second wing tip;
tail booms consisting of first, second, and third tail booms, each of the first tail boom, the second tail boom, and the third tail boom having a proximal end and a distal end, the proximal ends of the first tail boom, the second tail boom, and the third tail boom being connected to the flexible wing at evenly spaced locations along the wingspan of the flexible wing such that the first tail boom is evenly spaced between the first wing tip and the midpoint, the second tail boom is evenly spaced between the second wing tip and the midpoint, and the third tail boom is positioned at the midpoint; and
first, second, and third tail sections, each of the first tail section, the second tail section, and the third tail section having at least one elevator, wherein the first tail section is coupled to the distal end of the first tail boom, the second tail section is coupled to the distal end of the second tail boom, and the third tail section is coupled to the distal end of the third tail boom.

2. The wing-twist aircraft of claim 1 , wherein each of the first tail boom, the second tail boom, and the third tail boom comprise a vertical stabilizer.

3. The wing-twist aircraft of claim 1 , wherein the propulsion device includes a propeller and an electric motor configured to rotate the propeller.

4. The wing-twist aircraft of claim 3 , wherein the propeller is mounted to the flexible wing in a tractor configuration.

5. The wing-twist aircraft of claim 1 , wherein the at least one elevator for each of the first tail section, the second tail section, and the third tail section impart a distributed twist profile throughout the flexible wing via the proximal ends of the first tail boom, the second tail booms, and the third tail boom connected to the flexible wing at the evenly spaced locations along the wingspan of the flexible wing.

6. The wing-twist aircraft of claim 1 , wherein each of the first tail section, the second tail section, and the third tail section comprises a rudder.

7. The wing-twist aircraft of claim 1 , wherein the first tail section, the second tail sections, and the third tail section are configured to adjust a lift distribution of the wing-twist aircraft by twisting the flexible wing to create a lateral roll moment.

8. The wing-twist aircraft of claim 1 , wherein the flexible wing is devoid of movable control surfaces.

9. The wing-twist aircraft of claim 1 , wherein the flexible wing does not include any movable control surfaces between the first wing tip and the second wing tip.

10. The wing-twist aircraft of claim 1 , wherein the first tail boom, the second tail boom, and the third tail boom include landing gear.

11. The wing-twist aircraft of claim 1 , wherein the first tail boom, the second tail boom, or the third tail boom is configured to carry an intelligence, surveillance, or reconnaissance (ISR) payload.

12. The wing-twist aircraft of claim 1 , wherein each of the first tail boom, the second tail boom, and the third tail boom comprise a horizontal stabilizer.

13. A method of controlling an aircraft through adjustment of lift distribution across a flexible wing, the aircraft comprising the flexible wing and tail sections consisting of a first tail section, a second tail section, and a third tail section, wherein:
the first tail section is coupled to a port side of the flexible wing via a first tail boom, the first tail boom being positioned evenly between a port side wing tip and a wingspan midpoint,
the second tail section is coupled to a starboard side of the flexible wing via a second tail boom, the second tail boom being positioned evenly between a starboard side wing tip and the wingspan midpoint, and
the third tail section is coupled to the flexible wing via a third tail boom, the third tail boom being positioned at the wingspan midpoint, the method comprising:
receiving, via a processor, a flight command to adjust a rolling moment of the aircraft;
controlling, in response to the flight command, a first elevator to assume a first position, wherein the first elevator is coupled to the first tail section; and
controlling, in response to the flight command, a second elevator to assume a second position that is different from the first position to twist the flexible wing to a predetermined wing-twist angle, wherein the second elevator is coupled to the second tail section,
wherein the predetermined wing-twist angle is selected to achieve a predetermined difference in lift coefficient between the port side and the starboard side.

14. A method of controlling an aircraft through adjustment of lift distribution on a flexible wing, the aircraft comprising the flexible wing and tail sections consisting of a first tail section, a second tail section, and a third tail section, wherein:
the first tail section is coupled to a port side of the flexible wing via a first tail boom, the first tail boom being positioned evenly between a port side wing tip and a wingspan midpoint,
the second tail section is coupled to a starboard side of the flexible wing via a second tail boom, the second tail boom being positioned evenly between a starboard side wing tip and the wingspan midpoint, and
the third tail section is coupled to the flexible wing via a third tail boom, the third tail boom being positioned at the wingspan midpoint, the method comprising:
receiving, via a processor, a flight command to adjust a rolling moment of the aircraft; and
controlling, in response to the flight command, a first elevator coupled to the first tail section and a second elevator coupled to the second tail section to achieve a predetermined elevator degree differential.

15. The method of claim 14 , wherein the first elevator and the second elevator are configured to twist the flexible wing to a predetermined wing-twist angle as a function of the predetermined elevator degree differential.

16. The method of claim 15 , wherein the predetermined wing-twist angle is selected to achieve a predetermined difference in lift coefficient between the port side and the starboard side.

17. The method of claim 15 , wherein the predetermined elevator degree differential is negative when the flight command is a command to roll left.

18. The method of claim 15 , wherein the predetermined elevator degree differential is positive when the flight command is a command to roll right.

Assignees

• Facebook Inc

Inventors

• Uhlig Daniel
• Kays Cory A
• Uleck Kevin
• Crouse Jr Gilbert L

Classifications

• B64U10/25

  Fixed-wing aircraft (VTOL aircraft B64U10/20) · CPC title

• B64D27/353

  using solar cells · CPC title

• B64U50/19

  using electrically powered motors · CPC title

• B64U50/31

  generated by photovoltaics · CPC title

• B64U30/40

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