Patent ID: 6497091
Filing Date: 2002-12-24
Classification: F02K

Abstract:
An ignitor for use with a rocket engine to provide hypergolic fluid directly to a combustion chamber, said ignitor comprising:a cartridge having a cavity with a length therein and an inlet and an outlet; a piston assembly moveable between a first position and a discharged position along the length of the cartridge within the cavity; and a supply of hypergolic fluid located within the cavity between the piston assembly and the outlet, wherein movement of the piston assembly from the first position to the discharged position expels at least some of the supply of hypergolic fluid out of the outlet; at least one purge groove located along an interior surface of the cartridge cavity, wherein when said piston assembly is in the discharged position, said purge groove provides a conduit for flow around the piston assembly from the ignitor inlet to the ignitor outlet.