Methods and apparatus for increasing aerodynamic performance of projectiles

• US 20030047645A1
• Filed: 05/28/2002
• Published: 03/13/2003
• Est. Priority Date: 05/25/2001
• Status: Active Grant

• Current Assignee: Omnitek Partners LLC
• Original Assignee: Omnitek Partners LLC
• Inventors: Rastegar, Jahangir S., Pelz, Richard B.
• Granted Patent: US 6,727,485 B2
• Time in Patent Office: Days
• US Class Current: 244/3.24
• CPC Class Codes: F42B 10/146 Fabric fins, i.e. fins comprising at least one spar and a fin cover made of flexible sheet material
• CPC Class Codes: F42B 10/38 Range-increasing arrangements F42B10/34, F42B14/06 and F42B15/105 take precedence
• CPC Class Codes: F42B 10/40 with combustion of a slow-burning charge, e.g. fumers, base-bleed projectiles
• CPC Class Codes: F42B 10/42 Streamlined projectiles
• CPC Class Codes: F42B 10/44 Boat-tails specially adapted for drag reduction

Abstract

A method for enhancing an aerodynamic performance of an unmanned projectile. The method including at least one of the following: (a) morphing a cross-sectional shape of the projectile after launch thereof; (b) morphing a longitudinal shape of the projectile after launch thereof; (c) bleeding a fluid at a base of the projectile during flight thereof: (d) varying a base cone angle of the projectile as a function of speed thereof; (e) deploying at least one wing from a body of the projectile after launch thereof; and (f) deploying a fin from the body of the projectile after launch thereof.

Claims

1. An unmanned projectile, the projectile comprising at least one of the following enhancements to increase its aerodynamic performance:

(a) means for morphing a cross-sectional shape of the projectile after launch thereof;

(b) means for morphing a longitudinal shape of the projectile after launch thereof;

(c) means for bleeding a fluid at a base of the projectile during flight thereof;

(d) means for varying a base cone angle of the projectile as a function of speed thereof;

(e) means for deploying at least one wing from a body of the projectile after launch thereof; and

(f) means for deploying a fin from the body of the projectile after launch thereof.

2. The projectile of claim 1, wherein the means for morphing the cross-sectional shape of the projectile comprises a retention means for retaining a skin of the projectile prior to launch and release means for releasing the retention after launch.

3. The projectile of claim 2, wherein the retention means comprises a plurality of separating elements disposed between and inner and outer skin of the projectile and connected thereto.

4. The projectile of claim 3, wherein the release means comprises a wire member having a charge thereon.

5. The projectile of claim 2, wherein the retention means comprises a plurality of structural elements having a fluid disposed in a cavity therein.

6. The projectile of claim 5, wherein the release means comprises a means for releasing pressure in the cavity to release at least a portion of the fluid therefrom.

7. The projectile of claim 2, wherein the retention means comprises a sabo disposed around an outer periphery of the projectile.

8. The projectile of claim 7, wherein the release means comprises means for discarding the sabo upon launch.

9. The projectile of claim 1, wherein the means for morphing a longitudinal shape of the projectile comprises a means for morphing a plurality of cross-sections of the projectile along a longitudinal length of the projectile to achieve a desired longitudinal shape.

10. The projectile of claim 1, wherein the means for bleeding a fluid at a base of the projectile comprises means for directing a fluid from a cavity between inner and outer skins of the projectile to a base of the projectile.

11. The projectile of claim 1, wherein the projectile has a base, the base having a plurality of panels that are movable relative to a body of the projectile to form an angle with the body, wherein the means for varying a base cone angle of the projectile comprises means for varying the angle of the plurality of panels relative to the body.

12. The projectile of claim 11, wherein the means for varying the angle of the plurality of panels comprises at least one circumferential member attached to each of the panels to restrain the panels at a predetermined angle with the body and a means for releasing the circumferential member.

13. The projectile of claim 11, wherein the means for varying the angle of the plurality of panels comprises at least one circumferential member attached to each of the panels to restrain the panels at a predetermined angle with the body and a means for varying the length of the circumferential member.

14. The projectile of claim 1, wherein the projectile comprises an outer skin having the at least one deployable wing restrained thereon, wherein the means for deploying at least one wing from a body of the projectile comprises means for releasing the retention of the at least one wing to deploy the same.

15. The projectile of claim 14, wherein the means for releasing the retention comprises a locking strip disposed on the skin and having a portion thereof which interferes with the wing to prevent its deployment and a release means for releasing the strip from interfering with the wing.

16. The projectile of claim 1, further comprising means for shaping the wing after deployment thereof.

17. The projectile of claim 1, wherein the projectile comprises an outer skin having the at least one deployable fin restrained thereon, wherein the means for deploying at least one fin from a body of the projectile comprises means for releasing the retention of the at least one fin to deploy the same.

18. The projectile of claim 17, wherein the means for releasing the retention comprises a locking strip disposed on the skin and having a portion thereof which interferes with the fin to prevent its deployment and a release means for releasing the strip from interfering with the fin.

19. The projectile of claim 1, further comprising means for shaping the fin after deployment thereof.

20. A method for enhancing an aerodynamic performance of an unmanned projectile, the method comprising at least one of the following:

(a) morphing a cross-sectional shape of the projectile after launch thereof;

(b) morphing a longitudinal shape of the projectile after launch thereof;

(c) bleeding a fluid at a base of the projectile during flight thereof;

(d) varying a base cone angle of the projectile as a function of speed thereof;

(e) deploying at least one wing from a body of the projectile after launch thereof; and

(f) deploying a fin from the body of the projectile after launch thereof.

21. The method of claim 20, wherein the morphing of the cross-sectional shape of the projectile comprises retaining a skin of the projectile prior to launch and releasing the retention after launch.

22. The method of claim 20, wherein the morphing of the longitudinal shape of the projectile comprises morphing a plurality of cross-sections of the projectile along a longitudinal length of the projectile to achieve a desired longitudinal shape.

23. The method of claim 20, wherein the bleeding of the fluid at a base of the projectile comprises directing a fluid from a cavity between inner and outer skins of the projectile to a base of the projectile.

24. The method of claim 20, wherein the projectile has a base, the base having a plurality of panels that are movable relative to a body of the projectile to form an angle with the body, wherein the varying of the base cone angle of the projectile comprises varying the angle of the plurality of panels relative to the body.

25. The method of claim 20, wherein the projectile comprises an outer skin having the at least one deployable wing restrained thereon, wherein the deploying of the at least one wing from a body of the projectile comprises releasing the retention of the at least one wing to deploy the same.

26. The method of claim 20, further comprising shaping the wing after deployment thereof.

27. The method of claim 20, wherein the projectile comprises an outer skin having the at least one deployable fin restrained thereon, wherein the deploying of the at least one fin from a body of the projectile comprises releasing the retention of the at least one fin to deploy the same.

28. The method of claim 20, further comprising shaping the fin after deployment thereof.