Method and apparatus for a rocket engine power cycle

1. A system for providing an oxidizer and a fuel to a combustion chamber of a rocket engine, comprising:

an engine;

a fuel supply system comprising a fuel pump adapted to pump a fuel to said engine;

an oxidizer supply system adapted to pump an oxidizer to said engine, including:

an oxidizer pump; and

at least one oxidizer transport line, wherein the oxidizer is pumped through said oxidizer transport line and through a coolant system heat exchanger to gain energy before entering said engine;

a coolant supply system adapted to pump a coolant to said engine, including:

a coolant pump;

a heat exchanger; and

at least one coolant transport line, wherein the coolant is pumped through said coolant transport line to said engine to transfer heat from said engine to said heat exchanger; and

a heat transfer system operable to transfer energy from the coolant to the oxidizer before the oxidizer enters said combustion chamber of said engine;

a power source for providing power to each of said coolant pump, said oxidizer pump, and said fuel pump;

wherein said coolant supply system transports the coolant adjacent a portion of said engine such that the coolant is in thermal contact with said portion of said engine and thus receives energy from said engine;

wherein said power source is powered by a transfer of energy from the coolant to the power source.

2. The system of claim 1 , wherein the coolant comprises nitrogen.

3. The system of claim 1 , wherein a cooling pump of said coolant supply system is located within said system to inhibit mixing of said fuel and said oxidizer before said fuel and said oxidizer enter said combustion chamber.

4. A system for cooling and providing an oxidizer and a fuel to a rocket engine, comprising:

an oxidizer supply system, wherein said oxidizer supply system supplies the oxidizer to the engine;

a cooling system operable to transfer thermal energy from the rocket engine to the oxidizer supply system;

a fuel supply system for providing the fuel to the engine; and

a power plant, wherein said power plant powers each of said fuel supply system, said oxidizer supply system, and said cooling system, and wherein said power plant is powered by energy received from said cooling system.

5. The system of claim 4 , further comprising:

a heat exchanger;

wherein said cooling system comprises a first pump and coolant transport lines to move the coolant;

wherein said oxidizer supply system comprises a second pump and oxidizer transport lines to move the oxidizer;

wherein the coolant moved in said coolant transport lines receives thermal energy from the engine as the coolant is pumped in thermal contact with a portion of the engine; and

wherein the coolant transfers a first portion of the thermal energy absorbed to the power plant and the coolant transfers a second portion of the thermal energy to the heat exchanger.

6. The system of claim 4 , wherein said cooling system moves an inert compound; and

wherein said cooling system includes a pump that is located relative to said fuel supply system and said oxidizer supply system, to prevent mixing of said fuel and said oxidizer before said fuel and said oxidizer reach said engine before the fuel and the oxidizer enter the engine.

7. The system of claim 4 , further comprising a heat exchanger; and

wherein said cooling system transfers energy to said oxidizer supply through said heat exchanger.

8. A system for providing an oxidizer and a fuel to a combustion chamber of a rocket engine, comprising:

an engine;

a fuel supply system comprising a fuel pump adapted to pump a fuel to said engine;

an oxidizer supply system comprising an oxidizer pump adapted to pump an oxidizer to said engine;

a coolant supply system comprising a coolant pump adapted to pump a coolant to said engine;

a power plant to provide power to each of said fuel pump, said oxidizer pump, and said coolant pump;

wherein said coolant supply system transports the coolant adjacent a portion of said engine such that the coolant is in thermal contact with said portion of said engine and thus receives energy from said engine; and

wherein the coolant transfers energy to said power plant, to provide power to said power plant.

9. The system of claim 8 , wherein said coolant transfers energy to said oxidizer such that said coolant returns to a liquid state.

10. The system of claim 8 , wherein said coolant supply system includes a pump, the pump being located relative to the fuel supply system and the oxidizer supply system to preventing mixing of said fuel and said oxidizer prior to said fuel and said oxidizer entering said engine.

11. A system for a chemical rocket engine, comprising:

at least one of a combustion chamber, a nozzle, or combinations thereof;

an oxidizer supply system operable to supply an oxidizer to the at least one of a combustion chamber, a nozzle, or combinations thereof; and

a cooling system having a cooling material consisting essentially of nitrogen and operable to transfer thermal energy from the at least one of a combustion chamber, a nozzle, or combinations thereof to the oxidizer supply system.

12. The system of claim 11 , wherein the oxidizer supply system includes a power plant and at least one of a state change, an expansion, or combinations thereof of the cooling material powers the power plant.

13. The system of claim 11 , further comprising:

a heat exchanger operable to allow a thermal energy transfer from the coolant material to the oxidizer.