Claims
- 1. A retarding and locking mechanism for use between a projectile and a control fin part in a missile, wherein the projectile is activatable to motion and guided in the control fin part and, after a predetermined movement of the projectile, the projectile is retarded and interlocks with the control fin part and forms together a unitary, or integrated body, wherein the projectile has a radially outwards directed shoulder and the control fin part has a radially inwards directed shoulder, and wherein an axially compressible substantially inelastic element is provided between the shoulders, wherein the axially compressible element retards the projectile to stop while simultaneously substantially inelastically expanding the element radially and locking the projectile to the control fin part.
- 2. The retarding and locking mechanism of claim 1, wherein the compressible element is lying in a standby position against the radially outwards directed shoulder.
- 3. The retarding and locking mechanism of claim 1, wherein the compressible element is lying in a standby position against the radially inwards directed shoulder.
- 4. The retarding and locking mechanism of claim 1, wherein the compressible element is in the form of an inelastically deformable sleeve.
- 5. The retarding and locking mechanism of claim 4, wherein the compressible sleeve is conical.
- 6. The retarding and locking of claim 4, wherein a collar is provided at at least one of the ends of the sleeve.
- 7. The retarding and locking mechanism of claim 1, wherein the projectile and the control fin part and the compressible element are cylindrical in the contact surfaces thereof.
- 8. The retarding and locking mechanism of claim 1, wherein the projectile, the control fin part, and the compressible element, independent of each other, on at least areas thereof comprise at least one of a polygonal surface, serrated surface, and rough surface.
- 9. The retarding and locking mechanism of claim 1, wherein the inwards directed shoulder comprises an outwards directed recess with respect to the internal surface of the control fin part.
- 10. The retarding and locking mechanism of claim 1, wherein the outwards directed shoulder comprises an inwards directed recess with respect to the external surface of the projectile.
- 11. The retarding and locking mechanism of claim 9, wherein the recesses, after interlocking, are axially staggered with respect to each other.
- 12. The retarding and locking mechanism of claim 1, wherein the projectile is a penetrator.
- 13. The retarding and locking mechanism of claim 10, wherein the recesses, after interlocking, are axially staggered with respect to each other.
Priority Claims (1)
Number |
Date |
Country |
Kind |
992739 |
Jun 1999 |
NO |
|
RELATED APPLICATIONS
This application claims the benefit of the Norwegian application 1999 2739 filed Jun. 4, 1999 and the international application PCT/NO00/00192 filed Jun. 2, 2000. This application is related to co-pending applications “RELEASE MECHANISM IN A MISSILE” Ser. No. 10/009,281 “TRANSLATION AND LOCKING MECHANISM IN A MISSILE” Ser. No. 10/009,283 and “PROPELLING DEVICE FOR A PROJECTILE IN A MISSILE” Ser. No. 09/980,944 all filed concurrently herewith.
PCT Information
Filing Document |
Filing Date |
Country |
Kind |
PCT/NO00/00192 |
|
WO |
00 |
Publishing Document |
Publishing Date |
Country |
Kind |
WO00/75602 |
12/14/2000 |
WO |
A |
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DE |
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FR |
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FR |
2236581 |
Apr 1991 |
GB |