# US 2016/0355250 A1 · Deployment mechanism

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- Number: US 2016/0355250 A1
- Document ID: US20160355250A1
- Status: Published application
- Kind: A1
- Application number: 15/172,710
- Filed: 2016-06-03
- Published: 2016-12-08
- Earliest claimed: 2015-06-05
- Assignees: Lockheed Martin Corporation
- Applicants: Lockheed Martin Corporation
- Inventors: Nicholas L. Barnes; Ryan M. Alderfer; Timothy J. Marley; Stephen J. Schober
- Web page: https://patentgrep.com/patent/US20160355250A1

## CPC

- B64U 30/12: Variable or detachable wings, e.g. wings with adjustable sweep
- B64U 80/10: with means for moving the UAV to a supply or launch location, e.g. robotic arms or carousels
- B64U 80/70: in containers (B64U80/60 takes precedence)
- F16C 2326/43: Aeroplanes; Helicopters
- B64U: UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- F16C: SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS

## 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.

## Claims

### Claim 1

A deployment mechanism, comprising a hinged mechanism that stows in a stacked configuration and deploys in a level configuration.

### Claim 2 (depends on 1)

The deployment mechanism of claim 1, wherein the hinged mechanism includes an inner wing mount and an outer wing mount.

### Claim 3 (depends on 2)

The deployment mechanism of claim 2, 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.

### Claim 4 (depends on 3)

The deployment mechanism of claim 3, wherein the inner wing mount is deployable by a pretensioning of a spring assembly, housed in a spring housing.

### Claim 5 (depends on 4)

The deployment mechanism of claim 4, wherein the spring assembly is a spiral spring that is pretensioned then retained using set screws.

### Claim 6 (depends on 4)

The deployment mechanism of claim 4, wherein set screws mount the outer wing mount to the spring housing.

### Claim 7 (depends on 4)

The deployment mechanism of claim 4, wherein the pretensioning of the spring assembly is transferred through a torque tube attached to the inner wing mount.

### Claim 8 (depends on 7)

The deployment mechanism of claim 7, wherein the inner wing mount, the outer wing mount and the torque tube are mounted to a mount with a single pin assembly.

### Claim 9 (depends on 8)

The deployment mechanism of claim 8, wherein the single pin assembly is provided through pin guides of the inner wing mount, the outer wing mount and the torque tube.

### Claim 10 (depends on 8)

The deployment mechanism of claim 8, 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.

### Claim 11 (depends on 10)

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

### Claim 12 (depends on 10)

The deployment mechanism of claim 10, wherein the mount is attached to an aircraft frame.

### Claim 13 (depends on 10)

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

### Claim 14 (depends on 7)

The deployment mechanism of claim 7, wherein the torque tube is attached to the inner wing by a pin and slot assembly.

### Claim 15 (depends on 7)

The deployment mechanism of claim 7, wherein the torque tube is attached to the inner wing mount by a spline assembly.

### Claim 16 (depends on 7)

The deployment mechanism of claim 7, wherein the torque tube is attached to the inner wing mount by a keyway assembly.

### Claim 17 (depends on 7)

The deployment mechanism of claim 7, further comprising a bearing sleeve provided between the inner wing mount and the outer wing mount.

### Claim 18 (depends on 1)

The deployment mechanism of claim 1, wherein aircraft wings are attached to the hinged mechanism.

### Claim 19

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.