Deployment mechanism

Patent metadata

Field	Value
Publication number	US-10112698-B2
Application number	US-201615172710-A
Country	US
Kind code	B2
Filing date	Jun 3, 2016
Priority date	Jun 5, 2015
Publication date	Oct 30, 2018
Grant date	Oct 30, 2018

Abstract

A deployment or hinge mechanism and, more particularly, a compact unmanned aerial vehicle (UAV) wing deployment mechanism is provided. The deployment mechanism includes a hinged mechanism that stows in a stacked configuration and deploys in a level configuration.

First claim

What is claimed is:

1. A deployment mechanism, comprising a hinged mechanism that stows in a stacked configuration and deploys in a level configuration, wherein
the hinged mechanism includes an inner wing mount and an outer wing mount,
the inner wing mount is deployable by a pretensioning of a spring assembly,
the pretensioning of the spring assembly is transferred through a torque tube attached to the inner wing mount, and
the inner wing mount, the outer wing mount and the torque tube are mounted to a mount with a single pin assembly.

2. The deployment mechanism of claim 1 , wherein the single pin assembly is provided through pin guides of the inner wing mount, the outer wing mount and the torque tube.

3. The deployment mechanism of claim 1 , wherein the torque tube is attached to the inner wing mount by a pin and slot assembly.

4. The deployment mechanism of claim 1 , wherein the torque tube is attached to the inner wing mount by a spline assembly.

5. The deployment mechanism of claim 1 , wherein the torque tube is attached to the inner wing mount by a keyway assembly.

6. The deployment mechanism of claim 1 , wherein the inner wing mount includes a ramped guide slot which is structured to allow both rotational movement and vertical movement of the inner wing mount with respect to the outer wing mount.

7. The deployment mechanism of claim 6 , wherein the spring assembly is housed in a spring housing.

8. The deployment mechanism of claim 7 , wherein the spring assembly is a spiral spring that is pretensioned then retained using set screws.

9. The deployment mechanism of claim 7 , wherein set screws mount the outer wing mount to the spring housing.

10. The deployment mechanism of claim 1 , wherein the inner wing mount, the outer wing mount and the torque tube are cylindrically shaped, and fit within the mount which is cylindrically shaped.

11. The deployment mechanism of claim 10 , wherein the inner wing mount, the outer wing mount and the torque tube are nested within the mount.

12. The deployment mechanism of claim 10 , wherein the inner wing mount and the outer wing mount are deployable at different sweep angles.

13. A deployment mechanism, comprising a hinged mechanism that stows in a stacked configuration and deploys in a level configuration, wherein
the hinged mechanism includes an inner wing mount and an outer wing mount,
the inner wing mount includes a ramped guide slot which is structured to allow both rotational movement and vertical movement of the inner wing mount with respect to the outer wing mount,
the inner wing mount is deployable by a pretensioning of a spring assembly, housed in a spring housing,
the pretensioning of the spring assembly is transferred through a torque tube is attached to the inner wing mount, and
a bearing sleeve is provided between the inner wing mount and the outer wing mount.

14. A deployment mechanism, comprising a hinged mechanism that when deployed, an inner wing mount is rotated counter to an outer wing mount, and deploys from a stacked configuration to a level configuration, the hinged mechanism includes a single pin assembly which mounts an inner wing mount, an outer wing mount and a torque tube to a mount.

15. The deployment mechanism of claim 14 , further comprising a bearing sleeve provided between the inner wing mount and the outer wing mount.

16. The deployment mechanism of claim 14 , wherein the single pin assembly is provided through pin guides of the inner wing mount, the outer wing mount and the torque tube.

17. The deployment mechanism of claim 14 , wherein the torque tube is attached to the inner wing mount by a pin and slot assembly.

18. The deployment mechanism of claim 14 , wherein the torque tube is attached to the inner wing mount by a spline assembly or a keyway assembly.

19. The deployment mechanism of claim 14 , further comprising a spring assembly transferring a pretensioning through the torque tube which is attached to the inner wing mount.

20. The deployment mechanism of claim 19 , wherein the spring assembly is housed in a spring housing.

Assignees

• Lockheed Corp

Inventors

• Barnes Nicholas L
• Alderfer Ryan M
• Marley Timothy J
• Schober Stephen J

Classifications

• B64U80/70

  in containers (B64U80/60 takes precedence) · CPC title

• B64C3/38

  Adjustment of complete wings or parts thereof · CPC title

• F16C2326/43

  Aeroplanes; Helicopters · CPC title

• B64C39/024

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

• B64C3/56 Primary

  Folding or collapsing to reduce overall dimensions of aircraft · CPC title