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US 10,030,951 B2Granted
Drag reduction system
AssigneeBAE SYSTEMS plc
InventorsDennis Joseph Flynn, Paul Martin Locking, Martin Johnson
Life of this patent
Estimating the term…
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.
Claims15
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.
4 more elements
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.
4 more elements
Dependencies are inferred from the claim text.