Slow cook off rocket igniter
AssigneeAerojet-General Corporation
InventorsMark P. Friedlander, III, Robert E. Black, III, Julia Venarchick
Life of this patent
Estimating the term…
Abstract
A gas generating propulsion system includes an igniter containing an igniter propellant and an auto igniter. A rocket motor is coupled to the igniter and has a housing containing a main propellant, a rocket motor throat and a nozzle. A release port extends through a portion of the rocket motor. This gas release port has a variable diameter through bore in fluid communication with the main propellant. In this way, the through bore has a variable area that forms an unobstructed open area with a cross-section effective to discharge gas generated by the main propellant such that a pressure increase within the housing remains below a safety value for the housing.
Claims19
A gas generating propulsion system, comprising:
- an igniter containing an igniter propellant;
- a rocket motor coupled to said igniter and having a housing containing a main propellant, a rocket motor throat and a nozzle;
- a volume of auto igniter in flame communication with at least one of said igniter propellant and said main propellant, said volume effective to substantially consume said igniter propellant without exceeding a maximum pressure design limit of said igniter;
- and
- a gas release port extending through a portion of said rocket motor, said gas release port having a variable diameter through bore in fluid communication with said main propellant, said through bore having a variable area that, in a safe operation position, forms an open area with a first cross-section effective to discharge gas generated by said main propellant such that a pressure increase within said housing remains below both a debris generating value and a propulsive thrust value for said rocket motor during transport and storage and, in an armed operation position, forms an obstructed area with a second cross-section effective to enable the system to generate a pressure increase and discharge high thrust combustion gases.
An ordnance comprising:
- an aerodynamic housing;
- an explosive charge contained within a forward portion of said aerodynamic housing;
- and
- a propulsion system contained within an aft portion of said aerodynamic housing wherein said propulsion system includes an igniter containing an igniter propellant and a volume of auto igniter effective to substantially consume said igniter propellant without exceeding a maximum pressure design limit of said igniter, a rocket motor coupled to said igniter and having a housing containing a main propellant, a rocket motor throat and a nozzle, and a gas release port extending through a portion of said rocket motor, said gas release port having a variable diameter through bore in fluid communication with said main propellant, said through bore having a variable area that forms an open area with a cross-section effective to discharge gas generated by said main propellant such that a pressure increase within said housing remains below both a debris generating value and a propulsive thrust value for said rocket motor during transport and storage.
A method to enhance safety of an ordnance during storage and transport comprising the steps of:
- providing an ordnance having an aerodynamic housing with an explosive charge contained within a forward portion of said aerodynamic housing and a propulsion system contained within an aft portion thereof;
- forming said propulsion system to have an igniter coupled to a rocket motor, said rocket motor including, in sequence aftward, a main propellant contained in a housing thereof, a throat and a nozzle;
- forming a through bore in said housing, said through bore having a variable diameter that when set in a first position has an open area with a cross-section effective to discharge gas generated by said main propellant whereby a pressure increase within said housing associated with the generated gas generates insufficient thrust to either generate debris or to dislodge said ordnance from a restraint;
- and
- disposing an auto igniter in flame communication with at least one of an igniter propellant contained within said igniter and said main propellant.
Dependencies are inferred from the claim text.