Aerial vehicle with deployable components

Patent metadata

Field	Value
Publication number	US-11884388-B2
Application number	US-202318149550-A
Country	US
Kind code	B2
Filing date	Jan 3, 2023
Priority date	Nov 11, 2015
Publication date	Jan 30, 2024
Grant date	Jan 30, 2024

Abstract

An unmanned aerial vehicle (UAV) having wings stowed against a fuselage of the UAV in a first arrangement is disclosed. Methods and systems for deploying the wings into a second arrangement are disclosed. For example, after a launch of the UAV, the UAV monitors for at least one pre-set condition. The at least one pre-condition being a pre-condition associated with deploying wings of the UAV into the second arrangement. Upon detecting the at least one pre-set condition, the wings of the UAV are deployed into a second arrangement. Deploying the wings comprises activating, in response to detecting the at least one pre-set condition associated with the UAV, a gearbox configured to transition the wings from the first arrangement to the second arrangement. Roll control may be maintained throughout launch and deployment.

First claim

The following is claimed:

1. A method of deploying an unmanned aerial vehicle (UAV), the method comprising:
detecting, after a launch of the UAV, at least one pre-set condition associated with deploying wings of the UAV, the UAV having wings stowed against a fuselage of the UAV in a first arrangement; and
deploying, upon detecting the at least one pre-set condition, the wings of the UAV into a second arrangement, wherein deploying the wings of the UAV further comprises:
activating, in response to detecting the at least one pre-set condition associated with the UAV, a gearbox configured to transition the wings from the first arrangement to the second arrangement.

2. The method of claim 1 , wherein the at least one pre-set condition comprises at least one of the following: velocity, acceleration, and leveling associated with the UAV upon determining that UAV has launched.

3. The method of claim 1 , further comprising adjusting a wing sweep angle after satisfying the at least one pre-set condition after deploying the wings of the UAV to the second arrangement.

4. The method of claim 1 , further comprising extending an outer section of each of the wings after the wings have been deployed into the second arrangement.

5. The method of claim 1 , further comprising deploying at least one additional flight component of the UAV after satisfying the at least one pre-set condition.

6. The method of claim 5 , wherein deploying the at least one additional flight component further comprises deploying a telescoping boom independently from the wings of the UAV.

7. The method of claim 6 , wherein deploying the telescoping boom further comprises deploying an antenna.

8. The method of claim 5 , wherein deploying the at least one additional flight component further comprises deploying at least one stabilizer.

9. The method of claim 1 , further comprising detecting that the UAV has launched as a tube-integrated unmanned system.

10. The method of claim 1 , further comprising detecting that the UAV has launched from an aircraft.

11. The method of claim 1 , further comprising maintaining roll control of the UAV while deploying the wings of the UAV.

12. The method of claim 1 , wherein deploying the wings of the UAV comprises deploying the wings of the UAV when it is determined that the UAV has traveled a certain distance after launching.

13. The method of claim 1 , wherein deploying the wings of the UAV further comprises adjusting wingspan of the UAV in a third arrangement after the wings transition to the second arrangement.

14. The method of claim 13 , wherein deploying the wings comprises deploying the wings in:
the first arrangement comprising a left wing section and a right wing section stowed against a fuselage of the UAV;
the second arrangement comprising the left wing section and the right wing section deployed for flight at a sweep deployment angle; and
the third arrangement comprising the left wing section and the right wing section telescopically expanded.

15. The method of claim 13 , further comprises activating a belt system for transitioning of the UAV from the second arrangement to the third arrangement.

16. The method of claim 13 , wherein adjusting the wingspan of the UAV further comprises extending and retracting an outer section of each of the wings and exposing an inner section of each of the wings.

17. The method of claim 14 , further comprising transitioning the wings from the second arrangement to the third arrangement after an additional pre-set condition has been met.

18. The method of claim 14 , further comprising actuating at least one control surface on the UAV while adjusting the wingspan in the third arrangement.

19. The method of claim 18 , further comprising maintaining roll control of the UAV in the expanded arrangement by actuating the at least one control surface on the wings of the UAV.

20. The method of claim 19 , further comprising maintaining roll control of the UAV in the expanded arrangement by actuating the at least one stabilizer.

Assignees

• Anduril Industries Inc

Inventors

• Alley Nicholas Robert
• Steele Joshua Lemming
• Williams Jesse Owen
• Kuehme Daniel
• Phillips Jonathan Caleb

Classifications

• B64U30/40

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

• B64U2101/30

  for imaging, photography or videography · CPC title

• B64U10/25

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

• B64C39/024

  of the remote controlled vehicle type, i.e. RPV · CPC title

• F16H7/02

  with belts; with V-belts · CPC title