Retractable rotary turret

• US 8,635,938 B2
• Filed: 05/25/2011
• Issued: 01/28/2014
• Est. Priority Date: 05/25/2011
• Status: Active Grant

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: Raytheon Company (Rtx Corporation)
• Inventors: King, William B., Isker, John D., Mckearn, Chaunchy F., Griffin, Eric J.
• Primary Examiner(s): Lee, Benjamin P
• Application Number:
  US13/115,350
• Publication Number:
  US 20120297969A1
• Time in Patent Office: 979 Days
• Field of Search: 244/1.R, 244/129.1, 244/130, 244/129.4, 244/121, 89/372.1, 89/11.1, 89/410.1, 250/234, 250/203.1, 250/208.1, 250/236
• US Class Current: 89/37.21
• CPC Class Codes: F41A 23/20 for disappearing guns
• CPC Class Codes: F41H 13/005 the high-energy beam being a laser beam

Abstract

The technology can include a retractable rotary turret system. The system includes a base comprising two support arms. The system further includes a turret platform that is a truncated sphere having a substantially flat side and a substantially spherical side. The turret platform includes a turret support ring rotary coupled to the two support arms and a turret device isolatively coupled to the turret support ring. The turret platform is rotatable along a first dimension for deployment of the spherical side and is rotatable along the first dimension for deployment of the flat side.

Claims

1. A retractable rotary turret system, the system comprising:

a base comprising two support arms;

a turret platform that is a truncated sphere having a substantially flat side and a substantially spherical side, the turret platform comprising;

a turret support ring rotary coupled to the two support arms; and

a turret device isolatively coupled to the turret support ring;

wherein the turret platform is rotatable along a first dimension for deployment of the spherical side and is rotatable along the first dimension for deployment of the substantially flat side, wherein the substantially flat side of the turret platform substantially conforms to a vehicle surface when the turret platform is in a stowed position.

2. The system of claim 1, wherein the turret device comprises:

a mirror drive assembly having a primary window in the spherical side of the turret platform; and

a coarse tracker assembly having a secondary window in the spherical side of the turret platform.

3. The system of claim 2, wherein a center axis of the primary window is off-set and parallel to a center axis of the secondary window.

4. The system of claim 2, wherein a center axis of the mirror drive assembly is off-set and parallel to a center axis of the turret platform.

5. The system of claim 2, wherein the primary window and the secondary window are curved to conform to an outer surface of the spherical side.

6. The system of claim 2, wherein the primary window and the secondary window are substantially flat.

7. The system of claim 1, further comprising:

a first mirror mounted within the base and for receiving optical energy from an optical energy system;

a second mirror mounted within a top portion of the first support arm for receiving the optical energy from the first mirror and for directing the optical energy along an axis parallel to the first support arm;

a third mirror mounted within a bottom portion of the first support arm for receiving the optical energy from the second mirror and for directing the optical energy through an opening in the turret platform;

a fourth mirror mounted within the turret platform for receiving the optical energy from the third mirror and directing the optical energy to the turret device;

a secondary mirror mounted within the turret device for receiving the optical energy from the fourth mirror and for expanding the optical beam path from the fourth mirror; and

a primary mirror mounted with the turret device for receiving the optical energy from the secondary mirror and recollimating or focusing the optical energy based on a beam application.

8. The system of claim 7, wherein the beam application is a sensing application and the telescope collimates the optical energy based on a target range.

9. The system of claim 7, wherein the beam application is a high energy weapon application and the primary mirror focuses the optical energy onto a target.

10. The system of claim 1, wherein the turret device comprises a high energy laser pointing and tracking system, wherein the high energy laser pointing and tracking system is usable during deployment of the spherical side of the turret platform.

11. The system of claim 1, wherein the turret device comprises a passive optical sensor for providing imagery in one or more spectral bands in visible and infrared regions.

12. The system of claim 1, wherein the turret device comprises a semi-active sensor for providing range finding or illuminated target tracking.

13. The system of claim 1, wherein the turret platform is rotatable along two axes, the first axis for deployment and aiming of the turret device, and the second axis for aiming of the turret device.

14. The system of claim 1, wherein the turret platform geometry is defined as a²=b(2R−

b), wherein;

a is ½

of a maximum span of a circular footprint of the stowed side of the turret platform flush with an external surface of a vehicle;

b is a maximum height of the spherical side when deployed from the vehicle; and

R is a radius of the turret platform.

15. A truncated sphere turret platform, the turret platform comprising:

a turret support ring rotary rotatable along an elevation axis; and

a turret device isolatively coupled to the turret support ring;

wherein the turret platform having a flat side and a spherical side, and wherein the turret platform is rotatable along the elevation axis for deployment of the spherical side and is rotatable along the elevation axis for deployment of the flat side, wherein the substantially flat side of the turret platform substantially conforms to a vehicle surface when the turret platform is in a stowed position.

16. The turret platform of claim 15, wherein the turret device comprises an off-axis telescope with a spherical mirror, a figure mirror, a conic mirror, an on-axis telescope with central obscuration, a refractive telescope, or any combination thereof.

17. The turret platform of claim 15, wherein the turret platform comprising a plurality of apertures in the deployed side of the turret platform.

18. The turret platform of claim 15, wherein the turret device comprising:

a mirror drive assembly having a primary window in the spherical side of the turret platform; and

a coarse tracker assembly having a secondary window in the spherical side of the turret platform,

wherein the primary window and the secondary window are mounted side-by-side in the spherical side of the turret platform.

19. A turret payload system, the system comprising:

a payload support ring rotary coupled to two support arms; and

a payload device isolatively coupled to the payload support ring; and

a payload windscreen shell in a shape of a truncated sphere having a substantially flat side and a substantially spherical side on opposite sides of each other;

wherein the turret payload system is rotatable along the elevation axis over a first dimension for deployment of the spherical side and is rotatable over a second dimension for deployment of the flat side, wherein the substantially flat side of the payload windscreen shell substantially conforms to a vehicle surface when stowed.

20. The turret payload system of claim 19, wherein the substantially spherical side of the payload windscreen shell provides a minimum protrusion outside a vehicle and maintains a maximum field of regard when deployed.