Compressed gas integrated power and thermal management system

1. A power and thermal management system of an aircraft, the power and thermal management system comprising:

a tank of compressed gas;

a heat exchanger configured to receive a portion of the compressed gas from the tank at a lower pressure than in the tank;

a first expansion valve upstream of the heat exchanger;

a first turbine configured to be driven by the compressed gas from the tank that passes through the heat exchanger;

a second expansion valve downstream of the heat exchanger and upstream of the first turbine;

a controller configured to adjust a flow of the compressed gas through the first expansion valve and the second expansion valve in order to control a cooling capacity of the heat exchanger;

a first electric generator configured to be mechanically powered by the first turbine;

a second electric generator; and

a second turbine configured to mechanically power the second electric generator, wherein the second turbine is configured to be driven by the compressed gas exhausted from the first turbine,

wherein the power and thermal management system for the aircraft is configured as a primary electric power source for a directed energy weapon external to the power and thermal management system, and

wherein the heat exchanger is configured to cool the directed energy weapon from an expansion of the compressed gas released from the tank.

2. The system of claim 1 further comprising a heat exchanger in the tank, wherein the heat exchanger in the tank is configured to transfer heat received from the directed energy weapon to the compressed gas within the tank.

3. The system of claim 1 further comprising a combustor configured to receive compressed gas from the tank via the heat exchanger, the combustor further configured to burn fuel mixed with the compressed gas from the tank, and the combustor further configured to exhaust into the first turbine.

4. The system of claim 1 , wherein one of the first and second electric generators is configured to generate AC, and the other of the first and second electric generators is configured to generate DC.

5. The system of claim 1 , wherein the system is an integrated power and thermal management system.

6. A power and thermal management system comprising:

a tank of compressed gas;

a heat exchanger configured to receive a portion of the compressed gas from the tank at a lower pressure than in the tank;

a first expansion valve upstream of the heat exchange;

a turbine configured to be driven by the compressed gas from the tank that passes through the heat exchanger;

a second expansion valve downstream of the heat exchanger and upstream of the turbine;

a controller configured to adjust a flow of the compressed gas through the first expansion valve and the second expansion valve in order to control a cooling capacity of the heat exchanger; and

an electric generator configured to be mechanically powered by the turbine,

wherein the system is configured as a primary electric power source for a load, and

wherein the heat exchanger is configured to cool the load from an expansion of the compressed gas released from the tank.

7. The system of claim 6 , wherein the load comprises a directed energy weapon, and wherein the system is configured as a sole electric power source for the directed energy weapon.

8. The system of claim 6 , wherein the tank, the turbine, the electric generator, and the heat exchanger are included in an apparatus configured to be worn by a person.

9. The system of claim 6 further comprising a heat exchanger inside of the tank, wherein the heat exchanger inside of the tank is configured to transfer heat to the compressed gas within the tank via a coolant loop.

10. The system of claim 6 , wherein the turbine is a first turbine, wherein the system further comprises a second turbine and a gearbox, wherein the first and the second turbines are configured to mechanically power the electric generator via the gearbox, and wherein the second turbine is further configured to be driven by the compressed gas exhausted from the first turbine.

11. The system of claim 6 further comprising a combustor configured to receive compressed gas from the tank via the heat exchanger, the combustor further configured to burn fuel mixed with the compressed gas from the tank, and the combustor further configured to exhaust into the turbine.

12. The system of claim 11 , wherein the combustor and the turbine are a first combustor and a first turbine, respectively, wherein the system further comprises a second combustor and a second turbine, the second combustor configured to receive compressed gas exhausted from the first turbine, the second combustor further configured to burn fuel mixed with the compressed gas, and the second combustor further configured to exhaust into the second turbine.

13. A method of providing power and thermal management, the method comprising:

releasing compressed gas from a tank into a heat exchanger;

controlling, via a controller, a flow of the compressed gas through a first expansion valve upstream of the heat exchanger;

transferring heat to the compressed gas in the heat exchanger from a load;

controlling, via the controller, the flow of the compressed gas through a second expansion valve downstream of the heat exchanger and upstream of a turbine;

controlling, via the controller, a cooling capacity of the heat exchanger by adjusting the flow of the compressed gas through the first expansion valve and the second expansion valve;

driving the turbine by the compressed gas that is heated in the heat exchanger;

powering an electric generator mechanically by the turbine; and

providing electric power generated by the electric generator to the load as a primary power source.

14. The method of claim 13 , wherein the releasing, the transferring, the driving, the powering, and the providing are performed at an altitude greater than 30,000 feet.

15. The method of claim 13 further comprising transferring heat from the load to the compressed gas in the tank via a heat exchanger located inside of the tank.

16. The method of claim 13 , wherein the driving the turbine by the compressed gas comprises mixing the compressed gas with fuel to form a mixture, combusting the mixture in a combustor, and driving the turbine with exhaust from the combustor.

17. The method of claim 13 further comprising reaching a target power generated by the turbine by controlling an amount of the compressed gas that flows to the turbine from the heat exchanger.