Aerojet Rocketdyne, Inc.

G&h Technology, Inc.

Douglas S Parker

Frederick E Dodd

Daniel P Cap

An injector element for a liquid propellant rocket engine includes an oxidizer conduit, a central cavity that is fluidly coupled with the oxidizer conduit downstream of the oxidizer conduit, a first annulus that at least partially surrounds the oxidizer conduit and is fluidly coupled with an ignition fluid supply downstream of the ignition fluid supply, and a second annulus that at least partially surrounds the oxidizer conduit and is fluidly coupled with a fuel supply downstream of the fuel supply. The second annulus is fluidly coupled between the first annulus and the central cavity.

Injector element for rocket engine

An engine start system includes a facility that has a ground based hydraulic pressurization system and a combustor of a liquid propellant rocket engine. The engine is fluidly coupled to the ground based hydraulic pressurization system. The liquid propellant rocket engine is operably detachable from the ground based hydraulic pressurization system.

Ground hydraulic system hypergolic slug injection

An optical fiber socket terminus (28) has a fiber tip (30) received within a tip holder (32) that is welded (41) to a socket tube (36) slidingly received within a socket shoulder (44). A coil spring (38) extends about socket tube (36) between tip holder (32) and shoulder 44. Stop 49 is welded to end portion of tube (36) providing limit to shoulder (44) movement. Pin terminus (10) has a fiber tip (18) that is received within alignment bushing (60) along with the socket tip (30) to achieve proper end relation of the optical fibers.

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Sacramento, CA, United States of America

Douglas S Parker