Common carrier munition

Patent metadata

Field	Value
Publication number	US-9797698-B2
Application number	US-201414913088-A
Country	US
Kind code	B2
Filing date	Aug 18, 2014
Priority date	Aug 20, 2013
Publication date	Oct 24, 2017
Grant date	Oct 24, 2017

Abstract

The invention relates to a common carrier munition ammunition device, more particularly to common carrier payload delivery shell.
There is provided a common carrier munition comprising a tail unit, a main body which comprises a payload cavity for receiving a payload, a fuze, and located between said main body and the fuze an ogive element, wherein the tail unit and main body comprise cooperatively engaging male and female threaded portions, wherein at least one of the threads is a shearable thread.

First claim

The invention claimed is:

1. A common carrier munition comprising a tail unit, a main body which comprises a payload cavity for receiving a payload, a fuze, and located between said main body and the fuze an ogive element, wherein the tail unit and main body comprise cooperatively engaging male and female threaded portions, wherein at least one of the threads is a shearable thread, wherein the ogive element is reversibly engaged with the fuze and main body, and a frangible link that retains the ogive element and main body in operable arrangement, such that upon an impact, said frangible link is caused to fail, and such that said shearable thread has a lower shear strength than the frangible link to allow for the shearable thread to fail during flight of the common carrier munition.

2. The munition according to claim 1 , wherein the main body comprises a threaded portion manufactured from a first material, and the tail unit comprises a threaded portion manufactured from second material, wherein the second material has a lower hardness value than the first material.

3. The munition according to claim 2 , wherein the first material is selected from a steel alloy and the second material is selected from aluminium or alloy thereof.

4. The munition according to claim 1 , wherein there is a locking ring located between the main body and said ogive element, to retain said payload within the payload cavity.

5. The munition according to claim 4 , wherein the locking ring and main body comprise cooperatively engaging threaded portions.

6. The munition according to claim 1 , wherein the ogive element has a forward end locatable with said fuze and an aft end locatable with said main body, wherein the internal diameter of the aft end of said ogive element is substantially the same as the internal diameter of said payload cavity.

7. The munition according to claim 1 , wherein the fuze is operably connected to at least one expulsion charge, wherein said charge is suspended in free space.

8. The munition according to claim 1 , wherein the payload cavity has substantially parallel walls, which extend from the intersection of the tail unit to the locking ring.

9. The munition according to claim 1 , wherein the payload is a modular unit.

10. The munition according to claim 9 , wherein the modular unit, is reversibly loadable from the aft end of the main body.

11. The munition according to claim 1 , wherein the payload is capable of being dispensed rearwardly from the main body, upon shearing the shearable thread.

12. A method of dispensing a payload from a munition according to claim 1 , comprising causing initiation of an expulsion charge, and causing shearing of the shearable thread, wherein the fuze is operably connected to the expulsion charge.

13. A common carrier shell comprising a tail unit, a main body which comprises a payload cavity for receiving a uniform payload, a fuze, and located between said main body and the fuze an ogive element, wherein the ogive element is reversibly engaged with the fuze and main body, wherein said payload is selected from a smoke, illumination or UAV payload, and a frangible link that retains the ogive element and main body in operable arrangement, such that upon an impact, said frangible link is caused to fail, and such that said shearable thread has a lower shear strength than the frangible link to allow for the shearable thread to fail during flight of the common carrier munition.

14. The common carrier shell according to claim 13 , wherein the uniform payload cavity has a fixed uniform volume, such that it may receive a fixed uniform volume payload, thereby allowing the carrier shell to be configured with a variety of interchangeable payloads.

15. A common carrier shell comprising:
a tail unit;
a main body including a uniform payload cavity for receiving a modular payload, wherein the payload is selected from a smoke, illumination or UAV payload;
a fuze;
an ogive element located between the main body and the fuze, wherein the tail unit and main body comprise cooperatively engaging threaded portions, wherein at least one of the threads is a shearable thread, wherein the ogive element is reversibly engaged with the fuze and main body; and
a frangible link that retains the ogive element and main body in operable arrangement, such that upon an impact, said frangible link is caused to fail, and such that said shearable thread has a lower shear strength than the frangible link to allow for the shearable thread to fail during flight of the common carrier munition.

16. The common carrier shell according to claim 15 , wherein the main body comprises a threaded portion manufactured from a first material, and the tail unit comprises a threaded portion manufactured from second material, wherein the second material has a lower hardness value than the first material.

17. The common carrier shell according to claim 15 , wherein the ogive element has a forward end locatable with said fuze and an aft end locatable with said main body, wherein the internal diameter of the aft end of said ogive element is substantially the same as the internal diameter of said payload cavity.

18. The common carrier shell according to claim 15 , wherein the ogive element is reversibly engaged with the fuze and main body.

19. The common carrier shell according to claim 15 , wherein the fuze is operably connected to at least one expulsion charge, wherein said charge is suspended in free space.

Assignees

• Bae Systems Plc

Inventors

• Adams Daniel Alexander
• Jones Matthew
• Burn Andy Oden
• Costin David John
• Mccombie Stuart Andrew
• Wainwright John
• Rumfitt Michael Shaun

Classifications

• F42B12/625 Primary

  a single submissile arranged in a carrier missile for being launched or accelerated coaxially; Coaxial tandem arrangement of missiles which are active in the target one after the other (with shaped or hollow charges F42B12/16) · CPC title

• F42B12/42

  of illuminating type, e.g. carrying flares · CPC title