Method and apparatus for a rocket engine power cycle

1. A system in communication with a rocket engine comprising:

a fuel supply system communicates fuel to the rocket engine;

a coolant supply system that supplies a coolant to the rocket engine; and

a power source that powers at least one of the fuel supply system and the coolant supply system the power source powered at least in part by energy received from the coolant supply system.

2. The system of claim 1 , further comprising:

an oxidizer supply system that supplies the oxidizer to the engine.

3. The system of claim 2 , wherein the oxidizer supply system is powered at least in part by the power source.

4. The system of claim 2 , wherein the coolant system transfers thermal energy from the rocket engine to the oxidizer supply system.

5. The system of claim 2 , wherein the oxidizer supply system further comprises:

at least one oxidizer transport line to transport the oxidizer from the oxidizer supply system to the engine; and

a pump that pumps the oxidizer through the at least one oxidizer transport line.

6. The system of claim 5 , wherein the coolant supply system comprises:

a coolant pump;

a heat exchanger; and

at least one coolant transport line, wherein the coolant is pumped through the coolant transport line to the rocket engine to transfer heat from the engine to the heat exchanger and the oxidizer is pumped through the oxidizer transport line and through the heat exchanger to gain energy before entering the engine.

7. The system of claim 6 , wherein the coolant pump of the coolant supply system forms a barrier by being located within the system between the fuel supply system and the oxidizer supply system to inhibit mixing of the fuel and the oxidizer before the fuel and the oxidizer enter the combustion chamber.

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

9. A rocket engine, comprising:

a thrust chamber assembly;

a fuel supply system that communicates fuel to the thrust chamber assembly;

an oxidizer supply system that communicates oxidizer to the thrust chamber assembly;

a coolant supply system that communicates coolant to the thrust chamber assembly;

a power source that powers at least one of the fuel supply system, the oxidizer supply system, the coolant supply system, or combinations thereof the power source powered at least in part by a transfer of energy from the coolant to the power source.

10. The rocket engine of claim 9 , wherein the coolant supply system transports the coolant adjacent to a portion of the thrust chamber assembly such that the coolant is in thermal contact with the portion of the thrust chamber assembly and thus receives energy from the thrust chamber assembly.

11. The rocket engine of claim 10 , further comprising:

a heat transfer system operable to transfer energy from the coolant to the oxidizer before the oxidizer enters a combustion chamber of the thrust chamber assembly.

12. The rocket engine of claim 9 , wherein the coolant supply system comprises:

a coolant pump;

a heat exchanger; and

at least one coolant transport line, wherein the coolant is pumped through the coolant transport line that is in thermal contact with the thrust chamber assembly to transfer heat from the thrust chamber assembly to the heat exchanger.

13. The rocket engine of claim 12 , wherein the oxidizer supply system comprises:

an oxidizer pump;

at least one oxidizer transport line wherein the oxidizer is pumped through the oxidizer transport line and through the heat exchanger to gain energy before entering the thrust chamber assembly.

14. The rocket engine of claim 12 , wherein the coolant pump of the coolant supply system forms a barrier by being located within the system between the fuel supply system and the oxidizer supply system to inhibit mixing of the fuel and the oxidizer before the fuel and the oxidizer enter the combustion chamber.

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

an oxidizer supply system that supplies the oxidizer to the rocket engine;

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

a power source that powers at least one of the oxidizer supply system and the cooling system; and

an energy transfer system operable to transfer energy from a coolant in the coolant system to, at least in part, power the power source.

16. The system of claim 15 , further comprising a fuel supply system that provides the fuel to the rocket engine.

17. The system of claim 16 , wherein the power source powers the fuel supply system, the oxidizer supply system, and the coolant system.

18. The system of claim 17 , further comprising:

a heat exchanger;

wherein the coolant system comprises a first pump and a coolant transport line passing through the heat exchanger to move the coolant;

wherein the oxidizer supply system comprises a second pump and an oxidizer transport line passing through the heat exchanger to move the oxidizer;

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

wherein the coolant transfers a first portion of the thermal energy absorbed to the power source and the coolant transfers a second portion of the thermal energy through the heat exchanger to the oxidizer transport line.

19. The system of claim 16 , wherein the cooling system moves an inert compound, and the cooling system includes a pump that is located between the fuel supply system and the oxidizer supply system to prevent mixing of the fuel and the oxidizer before the fuel and the oxidizer enter the rocket engine.

20. The system of claim 15 , further comprising:

a heat exchanger; and

wherein the coolant system transfers energy to the oxidizer supply through the heat exchanger.