Rocket engine

Power plants – Reaction motor – Method of operation

Patent

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Details

60230, 60232, 60257, 60258, B63H 1100

Patent

active

061452998

ABSTRACT:
A liquid fuel rocket engine wherein the thrust producing exhaust of the engine is directed out of the engine in an annular fashion providing increased thrust and 360 degree thrust vectoring, while presenting the ability to be adaptable to different fuel/oxidizer mixtures, and prevent the sinusoidal shock wave formation typically associated with bell nozzle type rocket engines.

REFERENCES:
patent: 3344605 (1967-10-01), Mageean et al.
patent: 3358453 (1967-12-01), Swet
patent: 3699772 (1972-10-01), Elverum, Jr.

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