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US 6,145,299 AGranted
Rocket engine
OwnerTimothy Fasanoinventor
Life of this patent
Estimating the term…
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.
Claims17
A rocket engine comprising:
- a source of liquid fuel;
- a means for atomizing the liquid fuel in fluid communication with the source of liquid fuel;
- a chamber defined by a substantially enclosing chamber wall, the chamber disposed adjacent to the means for atomizing the liquid fuel in atomized fuel receiving relationship;
- a source of liquid oxidizer;
- a ring mounted on the substantially enclosing chamber wall defining a plurality of apertures, the plurality of apertures connected to the source of liquid oxidizer, the plurality of apertures substantially surrounding the chamber and disposed to admit the liquid oxidizer into the chamber;
- a housing having at least one substantially conical wall;
- a plurality of members attached to the housing in substantially radial array, and disposed within the chamber, and each of the plurality of members attached to the chamber walls holding the housing in fixed position with respect to the chamber;
- a conical surface disposed within the chamber, the surface forming substantially the top portion of the housing;
- a substantially annular passage defined by the wall of the housing and the substantially enclosing chamber wall, the combustion gasses passing through the annular passage, out to the ambient surroundings of the rocket.
6 more elements
The rocket engine of claim I wherein the conical surface is radially movable.
A method of providing rocket thrust comprising:
- atomizing liquid fuel;
- admitting the atomized fuel into a chamber defined by a substantially enclosing chamber wall;
- admitting an oxidizer from a ring mounted on the substantially enclosing chamber wall defining a plurality of apertures;
- combusting the fuel proximate a housing conical surface disposed within the chamber;
- and exhausting the combustion products through a substantially annular passage defined by the wall of the housing and the substantially enclosing chamber wall, the combustion gasses passing through the annular passage, out to the ambient surroundings of the rocket producing the thrust.
2 more elements
Dependencies are inferred from the claim text.