Integrated vehicle fluids with hot gas line and cold gas line merging to increase enthalpy
A system and methods are disclosed for an upper stage space launch vehicle that uses gases from the propellant tanks to power an internal combustion engine that produces mechanical power for driving other components including a generator for generation of electrical current for operating compressors and fluid pumps and for charging batteries. These components and others comprise a thermodynamic system from which system enthalpy may be leveraged by extracting and moving heat to increase the efficient use of propellant and the longevity and performance of the launch vehicle.
1. A thermodynamic system associated with an upper stage of a launch vehicle, comprising:
a gas line extending from a tank of the upper stage of the launch vehicle, the gas line configured to receive a gas fluid from the tank;
a hot line and a cold line that extend from the gas line, wherein each of the hot line and the cold line are configured to receive at least some of the gas fluid, and wherein the gas fluid in the hot line is configured to receive heat to increase an enthalpy of the gas fluid in the hot line;
a joint where the hot line and the cold line merge to form a combined gas fluid, and a thruster line configured to transfer the combined gas fluid to a thruster assembly having at least one thruster;
a hot thruster valve on the hot line that controls a flow rate of the gas fluid through the hot line to the thruster assembly; and
a cold thruster valve on the cold line that controls a flow rate of the gas fluid through the cold line to the thruster assembly;
wherein the hot thruster valve and the cold thruster valve control an enthalpy increase of the combined gas fluid, and wherein the at least one thruster of the thruster assembly vents or combusts the combined gas fluid.
2. The system of claim 1 , further comprising:
a coolant line having a coolant fluid;
a heat source configured to transfer heat to the coolant fluid in the coolant line; and
a heat exchanger configured to transfer heat from the coolant fluid in the coolant line to the gas fluid in the hot line, which increases the enthalpy of the gas fluid in the hot line.
3. The system of claim 2 , further comprising:
a pressurant line returning to the tank, wherein the pressurant line is configured to transmit at least some of the gas fluid with increased enthalpy to the tank to increase a pressure in the tank.
4. The system of claim 3 , further comprising:
a hot pressurant valve on the hot line that controls a flow rate of the gas fluid through the hot line to the tank;
a cold pressurant valve on the cold line that controls a flow rate of the gas fluid through the cold line to the tank; and
wherein the hot pressurant valve and the cold pressurant valve control an enthalpy increase of gas fluid transmitted to the tank.
5. The system of claim 2 , wherein the heat source is an internal combustion engine (ICE), and an ICE line transmits at least some of the gas fluid with increased enthalpy to the ICE.
6. The system of claim 5 , wherein the ICE turns a shaft, and the shaft turns a generator to produce electric power.
7. The system of claim 2 , wherein the heat exchanger has a first space and has a second space in thermal communication with the first space via an interface between the first space and the second space, wherein the coolant fluid is configured to flow through the second space, and the gas fluid in the hot line is configured to flow through the first space.
8. The system of claim 7 , further comprising:
a compressor having an impellor that is configured to rotate about an axis to create a pressure differential in the gas fluid in the hot line, wherein the impellor is configured to draw in the gas fluid along the axis and is configured to expel the gas fluid in an outward direction away from the axis to induce a rotation in the gas fluid, and wherein the rotating gas fluid is configured to flow through the first space such that a denser, colder portion of the gas fluid is positioned against the interface.
9. The system of claim 1 , further comprising:
a liquid line extending from the tank of the upper stage of the launch vehicle, the liquid line configured to receive a liquid fluid from the tank; and
a mixer valve associated with the gas line and the liquid line, wherein the mixer valve is configured to introduce liquid fluid to the gas fluid in the gas line, and the liquid fluid is configured to receive heat from a heat exchanger to vaporize at least some of the liquid fluid to change the enthalpy of the gas fluid.
10. The system of claim 9 , wherein the mixer valve comprises a body that defines an interior space to receive the liquid fluid, and the mixer valve comprises at least one port in fluid communication with the interior space to dispense the liquid fluid into the gas line.
11. A thermodynamic system associated with an upper stage of a launch vehicle, comprising:
a liquid line extending from a tank of the upper stage of the launch vehicle, the liquid line configured to receive a liquid fluid from the tank;
a gas line extending from the tank of the upper stage of the launch vehicle, the gas line configured to receive a gas fluid from the tank and configured to receive the liquid fluid from the liquid line;
a heat exchanger configured to transfer heat from a coolant fluid to the gas fluid and the liquid fluid in the gas line to vaporize at least some of the liquid fluid and increase the enthalpy of the gas fluid; and
a thruster assembly configured to receive the gas fluid with increased enthalpy, and wherein at least one thruster of the thruster assembly vents or combusts the gas fluid with increased enthalpy.
12. The system of claim 11 , further comprising:
a compressor configured to operate in a first mode where the compressor is configured to create a pressure differential in the gas fluid and the liquid fluid in the gas line, and the compressor is configured to operate in a second mode where the compressor is configured to not create a pressure differential in the gas fluid and the liquid fluid in the gas line, wherein the heat exchanger is configured to transfer heat and vaporize at least some of the liquid fluid in the gas line when the compressor is in the second mode.
13. The system of claim 12 , further comprising:
a hot line and a cold line that extend from the gas line, wherein gas fluid and liquid fluid in the hot line are configured to receive heat from the heat exchanger;
a joint where the hot line and the cold line merge to form the gas fluid that is transmitted to the thruster assembly;
a hot thruster valve on the hot line that controls a flow rate of fluid through the hot line to the thruster assembly; and
a cold thruster valve on the cold line that controls a flow rate of fluid through the cold line to the thruster assembly;
wherein the hot thruster valve and the cold thruster valve control an enthalpy increase of the gas fluid that is transmitted to the thruster assembly.
14. The system of claim 13 , further comprising:
a hot pressurant valve on the hot line that controls a flow rate of fluid through the hot line to the tank;
a cold pressurant valve on the cold line that controls a flow rate of fluid through the cold line to the tank; and
wherein the hot pressurant valve and the cold pressurant valve control an enthalpy increase of gas fluid transmitted to the tank to increase a pressure in the tank.
15. The system of claim 11 , further comprising:
a pressurant line returning to the tank, wherein the pressurant line is configured to transmit at least some of the gas fluid with increased enthalpy to the tank to increase a pressure in the tank.
16. The system of claim 11 , further comprising:
a coolant line having the coolant fluid; and
a heat source configured to transfer heat to the coolant fluid in the coolant line.
17. The system of claim 16 , wherein the heat source is an internal combustion engine (ICE), and an ICE line transmits at least some of the gas fluid with increased enthalpy to the ICE.
18. The system of claim 17 , wherein the ICE turns a shaft, and the shaft turns a generator to produce electric power.
19. The system of claim 13 , wherein the heat exchanger has a first space and has a second space in thermal communication with the first space via an interface between the first space and the second space, wherein the coolant fluid is configured to flow through the second space, and the gas fluid in the hot line is configured to flow through the first space.
20. The system of claim 11 , further comprising:
a mixer valve associated with the gas line and the liquid line, wherein the mixer valve is configured to introduce liquid fluid to the gas fluid in the gas line.