Rocket Propulsion Systems, and Related Methods
OwnerJordin Kareinventor
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Abstract
In an aspect of the invention, a system for rocket propulsion includes a heater operable to generate thermal energy from energy supplied from a non-chemical energy source, and to supply the thermal energy to a non-cryogenic fuel to thermally decompose the fuel into components that include at least a first component and a second component. The rocket propulsion system also includes a combustion chamber and a nozzle. The combustion chamber is operable to receive an oxidizer and at least a portion of the thermally decomposed fuel, and allow the two to combust. The nozzle generates thrust by directing the products of the combustion out of the system.
Claims22
A system for rocket propulsion, the system comprising:
- a heater operable to generate thermal energy from energy supplied from a non-chemical energy source, and to supply the thermal energy to a non-cryogenic fuel to thermally decompose the fuel into components that include at least a first component and a second component;
- a combustion chamber operable to receive an oxidizer and at least a portion of the thermally decomposed fuel, and to allow the two to combust;
- and
- a nozzle through which products of the combustion flow to generate thrust.
A method for producing rocket thrust, the method comprising:
- providing a heater energy from a non-chemical energy source;
- supplying thermal energy via the heater to thermally decompose a non-cryogenic fuel into components that include at least a first component and a second component, before the fuel enters a combustion chamber;
- mixing at least a portion of the decomposed fuel with an oxidizer to combust the two;
- and
- directing the products of combustion through a nozzle to generate thrust.
Dependencies are inferred from the claim text.