Selectable ramjet propulsion system

• US 9,726,115 B1
• Filed: 01/23/2012
• Issued: 08/08/2017
• Est. Priority Date: 02/15/2011
• Status: Active Grant

• Current Assignee: Aerojet Rocketdyne Inc. (L3Harris Technologies, Inc.)
• Original Assignee: Aerojet Rocketdyne Inc. (L3Harris Technologies, Inc.)
• Inventors: Hewitt, Patrick W., Mamula, Mark
• Primary Examiner(s): Bui Pho, Pascal M
• Assistant Examiner(s): Amar, Marc
• Application Number:
  US13/355,949
• Time in Patent Office: 2,024 Days
• Field of Search: 60250-255, 60219, 60234, 60224, 60225
• CPC Class Codes: F02K 7/18 Composite ram-jet/rocket engines
• CPC Class Codes: F02K 9/26 Burning control F02K9/10, F02K9/34, F02K9/86, F02K9/92 and F02K9/94 take precedence
• CPC Class Codes: F02K 9/28 having two or more propellant charges with the propulsion gases exhausting through a common nozzle

Abstract

A selectable ramjet propulsion system for propelling a rocket or missile includes a gas generator adjacent a booster. A frangible diaphragm is disposed between the gas generator and the booster. The booster and fuel gas generator can be operated in normal sequence, or operated at the same time in order to increase the thrust produced for short-range missions. A logic circuit contained on the rocket or missile determines a time to rupture the frangible diaphragm based on whether or not the distance to the target exceeds a threshold distance.

Claims

1. A selectable ramjet propulsion system for propelling a missile, comprising:

a variable flow ducted rocket having a gas generator, a combustor, a frangible diaphragm, and an inlet duct, wherein the a gas generator has a center-perforated grain solid rocket propellant, wherein the center-perforated grain solid rocket propellant of the gas generator is a ramjet fuel, wherein the gas generator is adjacent the combustor, wherein the combustor has a center-perforated grain solid rocket propellant, wherein the frangible diaphragm is disposed between said gas generator and said combustor, wherein the frangible diaphragm is configured to withstand an approximate 2000 psia boost pressure from the combustor, yet to yield upon a pressure lower than the boost pressure from the gas generator prior to an ignition of the center-perforated grain solid rocket propellant of the combustor, wherein the inlet duct is selectively fluidly coupled to the combustor via a port cover, and wherein the surface area of the frangible diaphragm is sized to allow an unchoked subsonic flow of a gaseous product of a combustion of the gas generator center-perforated grain solid rocket propellant into the combustor.

2. A method for operating a selectable ramjet propulsion system, for propelling a missile, having a gas generator adjacent a combustor of a booster and a frangible diaphragm disposed between said gas generator and said booster combustor, comprising the steps of:

igniting a booster combustor propellant contained within said booster;

determining a distance to an intended target; and

determining a time to ignite the gas generator fuel and rupture said frangible diaphragm based on said distance to target, and wherein the selectable ramjet propulsion system comprises;

a variable flow ducted rocket having the gas generator, the booster combustor, the frangible diaphragm, and an inlet duct, wherein the gas generator fuel is a center-perforated grain solid rocket propellant, wherein the center-perforated grain solid rocket propellant of the gas generator is a ramjet fuel, wherein the booster combustor propellant is a center-perforated grain solid rocket propellant, wherein the frangible diaphragm is configured to withstand an approximate 2000 psia boost pressure from the booster combustor, yet to yield upon a pressure lower than the boost pressure from the gas generator prior to an ignition of the center-perforated grain solid rocket propellant of the booster combustor, wherein the inlet duct is selectively fluidly coupled to the booster combustor via a port cover, and wherein the surface area of the frangible diaphragm is sized to allow an unchoked subsonic flow of a gaseous product of a combustion of the gas generator center-perforated grain solid rocket propellant into the booster combustor.

3. The method of claim 2 wherein said gas generator is activated and said frangible diaphragm is ruptured prior to consumption of said booster combustor propellant if said distance to an intended target is less than a threshold distance.

4. The method of claim 3 wherein said gas generator is activated and said frangible diaphragm is ruptured prior to ignition of said booster combustor propellant.

5. The method of claim 2 wherein said gas generator is activated and said frangible diaphragm is ruptured subsequent to consumption of said booster combustor propellant if said distance to an intended target exceeds a threshold distance.