Lockheed Martin Corporation

Ryan Earl Roberts

Darren Andrew Kearney

Rory Nell McLeod

Joseph Paul Arves

Herbert Stephen Jones

Herbert Stephens Jones

A rocket engine ( ) generates a flow of hot propulsion fluid through a nozzle ( N) for generating propulsive thrust along a thrust vector Hybrid exhaust gas generators ( ) have their exhausts ( ) through the side of the nozzle. Each gas generator includes a fuel grain ( ) and a source of oxidizer ( ). The fuel grain is kept hot by either or both (a) direct radiation or conduction from the hot propulsion fluid, or (b) by a trickle of oxidizer. The fuel grain can thus react quickly to a substantial flow of oxidizer.

Hybrid injection thrust vector control

A rocket engine ( ) generates a flow of hot propulsion fluid through a nozzle ( N). Hybrid exhaust gas generators ( ) have their exhausts ( ) through the side of the nozzle. Each gas generator includes a fuel grain ( ) and a source of oxidizer ( ). The fuel grain is kept hot by either or both (a) direct radiation or conduction from the hot propulsion fluid, or (b) by a trickle of oxidizer. When the thrust vector is to be modified, the appropriate one of the hybrid gas generators receives a flow of oxidizer, and the resulting exhaust gas is injected through the side of the nozzle.

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Meraux, LA, United States of America

Ryan Earl Roberts