Single-actuator rotational deployment mechanism for multiple objects

Patent metadata

Field	Value
Publication number	US-11644287-B2
Application number	US-201916440248-A
Country	US
Kind code	B2
Filing date	Jun 13, 2019
Priority date	Jun 13, 2019
Publication date	May 9, 2023
Grant date	May 9, 2023

Abstract

A deployment system, such as for deploying wings, includes a pair of hub assemblies that transmit linear motion provided by an actuator into a combination of rotational and axial motion. The actuator works on both hub assemblies, rotating (for each wing) a slew ring that is coupled to a lift bar that acts as a follower, following a pair of cam slots, to allow the wings to follow their desired course. In one embodiment the wings move axially away from a fuselage at the beginning of the deployment movement, followed by a primarily rotational movement, with the wings pulling in toward the fuselage at the end of the deployment process. The actuator includes a pair of threaded shafts (threaded in opposite directions) that rotate along with a pinion gear, driven by a motor, to translate a pair of retractor links that are coupled to the slew rings.

First claim

What is claimed is:

1. A deployment system comprising:
a mount configured to receive a device to be deployed;
a hub assembly that includes a tube having a cam slot; and
an actuator configured to rotate the mount relative to the tube;
wherein when the actuator causes the mount to rotate relative to the tube, a follower engaging the cam slot causes the mount to move both axially and rotationally relative to the tube;
wherein the tube is an outer tube;
wherein the hub assembly further includes an inner tube within the outer tube, wherein the inner tube is connected to the mount and moves along with the mount;
wherein the hub assembly further includes a tension rod located along a central axis of the hub assembly, wherein the tension rod mechanically engages the inner tube and the mount;
wherein the tension rod has opposite first and second threaded ends;
wherein the first threaded end has a pair of nuts thereon that bear on opposite major surfaces of a platform that is within the inner tube; and
wherein the second threaded end threadedly engages the mount.

2. The deployment system of claim 1 , wherein the tension rod has a spring therearound that provides a biasing force between the inner tube and the mount.

3. A deployment system comprising:
a mount configured to receive a device to be deployed;
a hub assembly that includes a tube having a cam slot; and
an actuator configured to rotate the mount relative to the tube;
wherein when the actuator causes the mount to rotate relative to the tube, a follower engaging the cam slot causes the mount to move both axially and rotationally relative to the tube;
wherein the follower is part of a bar that passes through the hub assembly;
wherein the cam slot is a first cam slot;
wherein the tube includes a second cam slot diametrically opposed to the first cam slot; and
wherein the cam slots each include a first portion that provides outward axial motion combined with rotational motion, and a second portion that provides inward axial motion combined with rotational motion;
further comprising a slew ring that is mechanically coupled to the actuator such that the actuator selectively rotates the slew ring about the hub assembly;
wherein the follower is part of a bar that passes through the hub assembly; and
further comprising walking links that mechanically couple the slew ring to the bar; and
wherein the slew ring, the walking links, and the bar all rotate as a unit about a central axis of the hub assembly;
wherein the walking links have ball-and-socket connections with the slew ring; and
wherein the walking links have cross-joint connections with ends of the bar.

4. A deployment system comprising:
a mount configured to receive a device to be deployed;
a hub assembly that includes a tube having a cam slot; and
an actuator configured to rotate the mount relative to the tube;
wherein when the actuator causes the mount to rotate relative to the tube, a follower engaging the cam slot causes the mount to move both axially and rotationally relative to the tube;
wherein the mount is a first mount;
wherein the hub assembly is a first hub assembly; and
further comprising:
a second mount configured to receive a second device to be deployed; and
a second hub assembly that includes a second hub having a second cam slot;

wherein the actuator is configured to rotate the second mount relative to the second hub; and
wherein when the actuator causes the second mount to rotate relative to the second hub, a second follower engaging the second cam slot causes the mount to move both axially and rotationally relative to the hub.

5. The deployment system of claim 4 , wherein the follower is part of a bar that passes through the first hub assembly.

6. The deployment system of claim 4 ,
wherein the follower is part of a bar that passes through the first hub assembly;
wherein the cam slot is a first cam slot;
wherein the tube includes a second cam slot diametrically opposed to the first cam slot; and
wherein the cam slots each include a first portion that provides outward axial motion combined with rotational motion, and a second portion that provides inward axial motion combined with rotational motion.

7. The deployment system of claim 6 , wherein the cam slots are J-shape cam slots.

8. The deployment system of claim 7 , wherein for each of the cam slots a terminus of the cam slot is substantially axial in orientation.

9. The deployment system of claim 8 , wherein for each of the cam slots the terminus has a reduced-width region, providing less clearance about the follower than other portions of the cam slot.

10. The deployment system of claim 6 , wherein circular cross-section ends of the bar engage the cam slots.

11. The deployment system of claim 4 ,
wherein the tube is an outer tube; and
wherein the first hub assembly further includes an inner tube within the outer tube, wherein the inner tube is connected to the mount and moves along with the mount.

12. The deployment system of claim 11 , wherein the first hub assembly further includes a tension rod located along a central axis of the first hub assembly, wherein the tension rod mechanically engages the inner tube and the mount.

13. The deployment system of claim 4 , further comprising a slew ring that is mechanically coupled to the actuator such that the actuator selectively rotates the slew ring about the first hub assembly.

14. The deployment system of claim 13 ,
wherein the follower is part of a bar that passes through the first hub assembly; and
further comprising walking links that mechanically couple the slew ring to the bar; and
wherein the slew ring, the walking links, and the bar all rotate as a unit about a central axis of the first hub assembly.

15. The deployment system of claim 13 , wherein the actuator includes a threaded shaft, driven by a motor, such that when the shaft is turned a link tube, coupled to the slew ring, that moves along the shaft.

16. The deployment system of claim 15 ,
wherein the actuator is a ball screw actuator,
wherein the ball screw actuator further includes a ball screw nut that is attached to the link tube, and
wherein the ball screw nut moves along the shaft, along with the link tube, as the link tube moves along the shaft.

17. The deployment system of claim 15 ,
wherein the actuator further includes gearing between a motor shaft of the motor, and the threaded shaft; and
wherein the gearing includes a driven gear having at least 120 teeth.

18. The deployment system of claim 4 ,
further comprising a frame to which the first hub assembly is attached and to which the actuator is mechanically coupled;
wherein the actuator is mechanically coupled to the frame by a hinge connection.

19. The deployment system of claim 4 ,
wherein the deployment system is a wing deployment system used to deploy wings that are attached to the mounts; and
wherein the wing deployment system is part of an aerial vehicle.

Assignees

• Raytheon Co

Inventors

• Travis Robert D

Classifications

• B64C3/56 Primary

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

• F42B10/14 Primary

  using fins spread or deployed after launch, e.g. after leaving the barrel · CPC title

• F42B15/01

  Arrangements thereon for guidance or control ({steering arrangements F42B10/60}; aircraft flight control B64C; guidance systems other than those installed aboard F41G7/00, F41G9/00; locating by use of radio or other waves G01S; flight control in general G05D1/00; computer aspects G06]) · CPC title

• F42B10/38

  Range-increasing arrangements (F42B10/34, F42B14/06 {and F42B15/105} take precedence) · CPC title