Drag reduction system

Patent metadata

Field	Value
Publication number	US-10030951-B2
Application number	US-201414895829-A
Country	US
Kind code	B2
Filing date	May 30, 2014
Priority date	Jun 4, 2013
Publication date	Jul 24, 2018
Grant date	Jul 24, 2018

Abstract

A drag reduction system, more specifically a forward mounted drag reduction system for use on an extended range artillery shell, includes a forward end comprising a fuse, an aft located base unit and located therebetween a shell body defining a cavity which comprises a payload, a forwardly located gas generator capable of generating a gas flow, and an ignition device to ignite the gas generator after the shell is launched.

First claim

The invention claimed is:

1. An extended range, gun-launched artillery shell, comprising:
a forward end comprising a fuze;
an aft located base unit;
a shell body located between the fuze and the base unit, the shell body defining a cavity which comprises a non-gas generating payload;
a forwardly located gas generator comprising a plurality of separate portions of an energetic material each configured to generate a gas flow; and
a plurality of ignition devices each configured to separately and independently activate the respective portion of the energetic material of the gas generator,
wherein the gas generator comprises a plurality of nozzles located on an ogive surface portion of the shell body adjacent to the fuze, each nozzle configured to be independently activated so as to provide directional control by causing an unsymmetrical laminar gas flow to reduce air resistance against the shell body.

2. The shell according to claim 1 , wherein the forwardly located gas generator is located between the fuze and the shell body.

3. The shell according to claim 1 , wherein the gas flow is directed along an outer surface of the shell body.

4. The shell according to claim 3 , wherein the gas flow is directed substantially rearwardly towards the aft base unit of the shell.

5. The shell according to claim 1 , wherein at least one of the nozzles is a directionable nozzle.

6. The shell according to claim 1 , wherein the gas generator provides a portion of gas flow which is substantially normal to the shell, to increase air resistance.

7. The shell according to claim 1 , wherein the gas generator is activated independent of the launch of the shell.

8. The shell according to claim 1 , wherein the plurality of nozzles includes at least one of a pyrotechnic controlling nozzle and a propellant gas controlling nozzle.

9. The shell according to claim 1 , wherein the energetic material includes at least one of a pyrotechnic composition and a propellant composition.

10. An extended range, gun-launched artillery shell, comprising:
a shell body defining a cavity configured to contain a non-gas generating payload;
a fuze located at a forward end of the shell body;
a base unit located at a rear end of the shell body;
a forwardly located gas generator comprising a plurality of separate portions of an energetic material each configured to generate a gas flow; and
a plurality of ignition devices each configured to separately and independently activate the respective portion of the energetic material of the gas generator,
wherein the gas flow generator comprises a plurality of nozzles located on an ogive surface portion of the shell body adjacent to the fuze, each nozzle configured to be independently activated so as to provide directional control by causing an unsymmetrical laminar gas flow to reduce air resistance against the shell body.

11. The shell according to claim 10 , wherein the forwardly located gas generator is located between the fuze and the shell body.

12. The shell according to claim 10 , wherein the gas flow is directed along an outer surface of the shell body.

13. The shell according to claim 10 , wherein the gas flow is directed substantially rearwardly towards the base unit of the shell.

14. The shell according to claim 10 , wherein the plurality of nozzles includes at least one of a pyrotechnic controlling nozzle and a propellant gas controlling nozzle.

15. The shell according to claim 10 , wherein the energetic material includes at least one of a pyrotechnic composition and a propellant composition.

Assignees

• Bae Systems Plc

Inventors

• Flynn Dennis Joseph
• Locking Paul Martin
• Johnson Martin

Classifications

• F42B10/40 Primary

  with combustion of a slow-burning charge, e.g. fumers, base-bleed projectiles · CPC title

• F42B10/668

  Injection of a fluid, e.g. a propellant, into the gas shear in a nozzle or in the boundary layer at the outer surface of a missile, e.g. to create a shock wave in a supersonic flow · CPC title

• F42B10/66

  Steering by varying intensity or direction of thrust (thrust vector control of rocket engine plants F02K9/80 {; guiding or controlling apparatus using jets adapted for cosmonautic vehicles B64G1/26}) · CPC title

• F42B10/666

  characterised by using a nozzle rotatable about an axis transverse to the axis of the projectile · CPC title