Aerial vehicle with deployable components

Patent metadata

Field	Value
Publication number	US-11541986-B2
Application number	US-201916700436-A
Country	US
Kind code	B2
Filing date	Dec 2, 2019
Priority date	Nov 11, 2015
Publication date	Jan 3, 2023
Grant date	Jan 3, 2023

Abstract

An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

First claim

What is claimed is:

1. A telescoping wing system for an aerial vehicle comprising:
an inner section configured to be stowed within an interior of an outer section in a first configuration; and
a telescoping mechanism configured to, after satisfaction of a pre-set condition, extend the outer section along a length of the inner section to increase a wingspan in a second configuration.

2. The telescoping wing system of claim 1 , wherein the pre-set condition comprises a set amount of time having passed after a detected launch.

3. The telescoping wing system of claim 1 , further comprising a control surface attached to a trailing-edge of the outer section, wherein the control surface attaches to the outer section via a hinge mounted on an external surface of the trailing-edge.

4. The telescoping wing system of claim 1 , wherein the inner section is attached to a fuselage of the aerial vehicle.

5. The telescoping wing system of claim 4 , wherein at least a portion of an increased wingspan of the aerial vehicle is comprised of approximately a length of the outer section and a length of an exposed portion of the inner section.

6. The telescoping wing system of claim 5 , wherein the length of the exposed portion of the inner section increases as the outer section is displaced by at least a portion of the length between a first end of the inner section and a second end of the inner section.

7. The telescoping wing system of claim 6 , wherein displacement of the outer section along the length of the exposed portion of the inner section extends the wingspan of the aerial vehicle by approximately the length of the exposed portion of the inner section to form the increased wingspan.

8. The telescoping wing system of claim 1 , wherein the inner section and the outer section are configured, in the first configuration, to be stowed against a fuselage of the aerial vehicle.

9. The telescoping wing system of claim 8 , wherein the inner section and the outer section are configured, in the first configuration, to be deployed at an angle relative to the fuselage of the aerial vehicle.

10. The telescoping wing system of claim 9 , wherein the inner section and the outer section are configured to transition from the first configuration to the second configuration at the angle into the second configuration.

11. The telescoping wing system of claim 1 , wherein the pre-set condition comprises a set distance after a detected launch.

12. The telescoping wing system of claim 1 , wherein the telescoping wing system is configured to dynamically adjust wing sweep angle after satisfaction of the pre-set condition.

13. The telescoping wing system of claim 1 , wherein the outer section is dynamically adjustable after the wingspan is in the second configuration.

14. The telescoping wing system of claim 1 , wherein the telescoping mechanism is configured for a telescoping boom.

15. The telescoping wing system of claim 14 , wherein the telescoping boom comprises an antenna.

16. The telescoping wing system of claim 1 , wherein the telescoping mechanism comprises a belt system.

17. The telescoping wing system of claim 16 , wherein the belt system is attached to the outer section to increase the wingspan to the second configuration.

18. The telescoping wing system of claim 1 , wherein the outer section comprises at least one flight control mechanism.

19. The telescoping wing system of claim 18 , wherein the at least one flight control mechanism provides increased roll control after extending the outer section.

20. The telescoping wing system of claim 18 , wherein the at least one flight control mechanism comprises trailing-edge hinged ailerons.

21. The telescoping wing system of claim 18 , wherein the at least one flight control mechanism maintains roll control as the outer section extends along the inner section.

22. The telescoping wing system of claim 1 , wherein the outer section extends to an intermediate position between the first configuration and the second configuration to decrease drag generated by the telescoping wing system.

Assignees

• Anduril Industries Inc

Inventors

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

Classifications

• Y02T50/10

  Drag reduction · CPC title

• B64C5/12

  for retraction against or within fuselage or nacelle · CPC title

• B64C3/54 Primary

  Varying in area · CPC title

• B64C2211/00

  Modular constructions of airplanes or helicopters · CPC title

• B64C13/30

  using cable, chain, or rod mechanisms · CPC title