Deployable fin projectile with outflow device

• US 6,695,252 B1
• Filed: 09/18/2002
• Issued: 02/24/2004
• Est. Priority Date: 09/18/2002
• Status: Expired due to Term

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: Raytheon Company (Rtx Corporation)
• Inventors: Dryer, Richard
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US10/246,082
• Time in Patent Office: 524 Days
• Field of Search: 244/91, 244/49, 244/87, 244/3-7-
• US Class Current: 244/3.28
• CPC Class Codes: F42B 10/14 using fins spread or deployed after launch, e.g. after leaving the barrel
• CPC Class Codes: F42B 10/20 deployed by combustion gas pressure, or by pneumatic or hydraulic forces

Abstract

A missile or projectile tail section includes an outflow device and a number of deployable fins. The outflow device may be a base bleed device that includes a slow-burning propellant which fills the vacuum created by the projectile'"'"'s motion through the air. Use of the outflow device may allow the projectile range to be extended by up to 20%. The fins are stowed canted relative to planes that include the axis of the tail section. By canting or tilting the fins relative to the axis of the tail section, increased space is made in the tail section for the outflow device. Although the fins are stowed canted relative to the tail section, they may be configured so as to be deployed such that the axis of the tail section is substantially within the planes of the fins.

Claims

1. A projectile tail section comprising:

an outflow device surrounding an axis of the tall section; and

a plurality of deployable, substantially planar fins stowed within the tail section around the outflow device;

wherein the axis of the tall section is not co-planar with planes of the fins, when the fins are stowed within the tail section; and

wherein the tall section includes a housing with slots therein, and wherein the fins are located in the slots when the fins are stowed.

2. The tall section of claim 1, wherein the fins are canted relative to the axis of the tail section, when the fins are stowed within the tail section.

3. The tail section of claim 1, wherein the fins are configured to be deployed during flight of the projectile.

4. The tail section of claim 3, wherein the fins are configured to be deployed during flight of the projectile such that the axis of the tail section is substantially within the planes of the fins, when the fins are deployed.

5. The tail section of claim 3, wherein the fins are configured to be deployed such that the axis of the tail section is not coplanar with planes of the fins, when the fins are deployed.

6. The tail section of claim 1, further comprising pins about which respective of the fins rotate during deployment.

7. The tail section of claim 6, wherein the pins are protrusions on the fins.

8. The tail section of claim 1, wherein the outflow device includes a rocket motor.

9. The tail section of claim 6, wherein the pins fit through holes in the fins.

10. The tail section of claim 9, wherein the holes in the fins are elongated holes, allowing rotation of the fin in planes that include a pin axis of the pin.

11. The tail section of claim 6, wherein fins are also operatively configured to rotate within a plane that includes an axis of the pin.

12. The tail section of claim 1, further comprising:

a piston; and

a linkage coupled to the piston and the fins;

wherein movement of the piston causes the fin to rotate about the pin.

13. The tail section of claim 12, wherein a piston chamber on one side of the piston is in communication with the outflow device.

14. The tail section of claim 1, further comprising locks that hold the fins in place, once the fins are deployed.

15. The tail section of claim 14, wherein the locks include spring-and-detent mechanisms.

16. The tail section of claim 1, wherein planes of the fins are offset from and substantially parallel the axis of the tail section, when the fins are stowed within the tail section.

17. The tail section of claim 1, wherein the outflow device includes a base bleed device.

18. The tail section of claim 1,

wherein the slots have openings with respective notches;

and

wherein the fins pass at least partially through respective of the notches when the fins are fully deployed.

19. The tail section of claim 1, wherein the fins include aft-deploying fins.

20. The tail section of claim 1, wherein the fins include forward-deploying fins.

21. The tail section of claim 1, in combination with a body of the projectile and a nose of the projectile.

22. The tail section of claim 1, wherein the plurality of fins includes eight fins.

23. A projectile tail section comprising:

an outflow device surrounding an axis of the tail section; and

a plurality of deployable, substantially planar fins stowed within the tail section around the outflow device; and

pins about which respective of the fins rotate during deployment;

wherein the pins are protrusions on the fins;

wherein the axis of the tail section is not co-planar with planes of the fins, when the fins are stowed within the tail section;

wherein the tail section includes a housing with wobble cavities therein; and

wherein the pins are configured to rotate about at least two axes within respective of the wobble cavities.

24. A projectile tail section comprising:

an outflow device surrounding an axis of the tail section; and

a plurality of deployable fins stowed in slots within the tail section, around the outflow device;

wherein the fins are canted relative to the axis of the tail section, when the fins are stowed within the tail section.

25. The tail section of claim 24, wherein the outflow device includes a base bleed device.

26. The tail section of claim 24, wherein the outflow device includes a rocket motor.

27. The tail section of claim 24, in combination with a body of the projectile and a nose of the projectile.

28. The tail section of claim 24, wherein the plurality of fins includes eight fins.

29. A method of deploying fins for a projectile, the method comprising:

moving the fins from a stowed configuration to a partially-deployed configuration; and

moving the fins from the partially-deployed configuration to a fully-deployed configuration;

wherein the fins are within slots in a tail section of the projectile when the fins are in the stowed configuration;

wherein the fins are canted relative to an axis of the tail section when the fins are in the partially-deployed configuration; and

wherein the axis of the tail section is substantially within planes of the fins, when the fins are in the fully-deployed configuration.

30. A The method of claim 29, wherein the moving the fins from the stowed configuration to the partially-deployed configuration includes rotating the fins about respective pins within the slots.

31. The method of claim 29, wherein the moving the fins from the partially-deployed configuration to the fully-deployed configuration includes rotating the fins about a rotation axis which is substantially parallel to the axis of the tail section.

32. A projectile tail section comprising:

an outflow device surrounding an axis of the tail section; and

a plurality of deployable, substantially planar fins stowed within the tail section around the outflow device;

wherein the axis of the tail section is not co-planar with planes of the fins, when the fins are stowed within the tail section; and

wherein the axis of the tail section is substantially co-planar with planes of the fins, when the fins are deployed.

33. The tail section of claim 32, wherein the plurality of fine includes eight fins.

34. The tail section of claim 32,

wherein the tail section includes a housing with slots therein; and

wherein the fins are located in the slots when the fins are stowed.