Drag reduction system

Patent metadata

Field	Value
Publication number	US-2016123711-A1
Application number	US-201414895829-A
Country	US
Kind code	A1
Filing date	May 30, 2014
Priority date	Jun 4, 2013
Publication date	May 5, 2016
Grant date	—

Abstract

The invention relates to a drag reduction system, more specifically a forward mounted drag reduction system for use on extended range artillery.
There is provided a long range artillery projectile having forward end comprising a fuze, an aft located base unit and located therebetween a projectile body defining 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; preferably at a predetermined time after the projectile is launched.

First claim

1 . An extended range artillery projectile having a forward end comprising a fuze, an aft located base unit, located therebetween a projectile body defining cavity which comprises a payload, and a forwardly located gas generator capable of generating a gas flow, said gas generator comprising an ignition device to activate the gas generator.

2 . A projectile according to claim 1 wherein the forwardly located gas generator is located between the fuze and the projectile body.

3 . A projectile according to claim 1 wherein the forwardly located gas generator is located on the ogive section between the fuze and the projectile body.

4 . A projectile according to claim 1 wherein the gas flow is directed along the outer surface of the projectile body.

5 . A projectile according to claim 4 , wherein the gas flow is directed substantially rearwardly towards the aft base unit of the projectile.

6 . A projectile according to claim 1 , wherein the gas generator comprises at least one nozzle.

7 . A projectile according to claim 6 wherein the gas generator comprises a plurality of nozzles equidistant around the circumference of the projectile.

8 . A projectile according to claim 7 , wherein the plurality of nozzles are each capable of being independently activated, so as to provide directional control by causing an unsymmetrical gas flow.

9 . A projectile according to claim 6 , wherein the at least one nozzle is a directionable nozzle.

10 . A projectile according to claim 1 , wherein the gas generator provides a portion of gas flow which is substantially normal to the projectile, to increase air resistance.

11 . A projectile according to claim 1 wherein the gas generator is activated independent of the launch of the projectile.

12 . A method of controlling the trajectory of a projectile during flight, the projectile having a forward end including a fuze, an aft located base unit, a projectile body located between the fuze and the base unit and defining a cavity which includes a payload, and a forwardly located gas generator capable of generating a gas flow, said gas generator including an ignition device to activate the gas generator, the method comprising:
activating the gas generator, directing the gas flow so as to alter said trajectory.

13 . (canceled)

14 . An extended range artillery projectile, comprising:
a projectile body defining a cavity which includes a payload; a fuze located at a forward end of the projectile body; a base unit located at a rear end of the projectile body; and a forwardly located gas generator configured to generate a gas flow, the gas generator including an ignition device to activate the gas generator.

15 . A projectile according to claim 14 wherein the forwardly located gas generator is located between the fuze and the projectile body.

16 . A projectile according to claim 14 wherein the forwardly located gas generator is located on the ogive section between the fuze and the projectile body.

17 . A projectile according to claim 14 wherein the gas flow is directed along the outer surface of the projectile body.

18 . A projectile according to claim 14 , wherein the gas flow is directed substantially rearwardly towards the base unit of the projectile.

19 . A projectile according to claim 14 , wherein the gas generator comprises at least one nozzle.

20 . A projectile according to claim 19 wherein the gas generator comprises a plurality of nozzles equidistant around the circumference of the projectile.

21 . A projectile according to claim 20 , wherein the plurality of nozzles are each capable of being independently activated, so as to provide directional control by causing an unsymmetrical gas flow.

Assignees

• Bae Systems Plc

Inventors

• Flynn Dennis Joseph
• Locking Paul Martin
• Johnson Martin

Classifications

• 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

• F42B10/668

  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

• F42B10/40 Primary

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

• F42B10/666

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