Hybrid injection thrust vector control
AssigneeLockheed Martin Corporation
InventorsHerbert Stephens Jones, Joseph Paul Arves, Darren Andrew Kearney, Ryan Earl Roberts, Rory Nell McLeod
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Abstract
A rocket engine (10) generates a flow of hot propulsion fluid through a nozzle (14N) for generating propulsive thrust along a thrust vector 8. Hybrid exhaust gas generators (36,38) have their exhausts (44,54) through the side of the nozzle. Each gas generator includes a fuel grain (46,56) and a source of oxidizer (16,40,50). 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.
Claims7
A vehicle, comprising:
- a source of main propulsion fluid;
- a nozzle coupled to said source of propulsion fluid, for generating propulsion thrust by discharge of said main propulsion fluid generally along a discharge axis;
- and
- a hybrid exhaust fluid generator including a solid grain, said hybrid exhaust fluid generator including an exit port coupled to a side of said nozzle at a first location, and also including an oxidizer input port, for generating secondary fluid at said exit port in response to reaction of said grain with oxidizer applied to said oxidizer input port, and for injecting said secondary fluid into said side of said nozzle for thereby deflecting said main propulsion thrust relative to said wherein said main propulsion fluid is at a high temperature, and said exit port is coupled to side of said nozzle in a such a manner that heat from said main propulsion fluid heats said grain, whereby said grain tends to combust readily with said oxidizer.
Dependencies are inferred from the claim text.