Small satellite propulsion system utilizing liquid propellant ullage vapor

Patent metadata

Field	Value
Publication number	US-12442350-B2
Application number	US-201615184854-A
Country	US
Kind code	B2
Filing date	Jun 16, 2016
Priority date	Jun 16, 2016
Publication date	Oct 14, 2025
Grant date	Oct 14, 2025

Abstract

A novel approach provides a small satellite propulsion system that uses vapor to generate thrust for the small satellite. The vapor naturally sits on top of liquid propellant(s), which are stored within a propellant tank. The vapor may flow from the propellant tank and through a membrane to interact with a reacting surface to generate thrust.

First claim

The invention claimed is:

1. An apparatus, comprising:
a propellant tank comprising liquid propellant with a reactive vapor phase,
a catalyst located downstream of the propellant tank along a vapor flow path, wherein
the propellant tank is configured to be selectively exposed to the pressure of space, generating a pressure differential causing a flow of vapor from the propellant tank and through a valve, a membrane, a collection of tubes, or a combination thereof,
to interact with the catalyst to generate thrust while maintaining the liquid propellant in the propellant tank; and
a propellant management device configured to prevent the liquid propellant from escaping the propellant tank and propagating through the apparatus.

2. The apparatus of claim 1 , wherein the liquid propellant continuously generates the reactive vapor phase until the liquid propellant is exhausted.

3. The apparatus of claim 1 , further comprising:
a separation membrane configured to prevent the liquid propellant from escaping the propellant tank and propagating through the apparatus.

4. The apparatus of claim 1 , wherein the apparatus further includes the valve,
the valve controls the flow of the reactive vapor phase from the propellant tank to the catalyst.

5. The apparatus of claim 1 , wherein the apparatus further includes the membrane,
the membrane comprises a plurality of pores to control the flow of the reactive vapor phase to the catalyst.

6. The apparatus of claim 5 , wherein the flow of the reactive vapor phase is dependent on a size of each of the plurality of pores.

7. The apparatus of claim 1 , wherein the apparatus further includes the membrane, the membrane comprises a thermal transpiration membrane.

8. The apparatus of claim 1 , wherein the apparatus further includes the collection of tubes, the collection of tubes is proximate to the
catalyst and controls the flow of reactive vapor phase from the propellant tank to the catalyst.

9. The apparatus of claim 1 , wherein the interaction of the reactive vapor phase and the catalyst generates high temperature gas.

10. The apparatus of claim 1 , wherein the apparatus further includes the membrane, the apparatus further comprising:
a thermal guard placed between the membrane and a cold chamber to maintain the reactive vapor phase in the cold chamber thermally separated from the catalyst.

11. The apparatus of claim 1 , further comprising:
a thermal connector transferring heat from a hot chamber to the propellant tank to maintain a minimum temperature of the liquid propellant and control pressure of the vapor.

12. An apparatus, comprising:
a first propellant tank comprising liquid propellant having a reactive vapor phase;
a catalyst located downstream of the propellant tank along a vapor flow path;
a valve, when open, causes the reactor vapor phase to be pulled from the first propellant tank and flow through a membrane to interact with the catalyst to generate thrust, wherein the first propellant tank is configured to be selectively exposed to the pressure of space, generating a pressure differential causing a flow of vapor from the first propellant
tank and through the valve, the membrane, a collection of tubes, or a combination thereof, to interact with the catalyst to generate thrust while maintaining the liquid propellant in the first propellant tank; and
a propellant management device configured to prevent the liquid propellant from escaping the first propellant tank and propagating through the apparatus.

13. The apparatus of claim 12 , wherein the liquid propellant continuously generates the reactive vapor phase until the liquid propellant is exhausted.

14. The apparatus of claim 12 , further comprising:
a separation membrane configured to prevent the liquid propellant from escaping the propellant tank and propagating through the apparatus.

15. The apparatus of claim 12 , wherein the membrane comprises a thermal transpiration membrane.

16. The apparatus of claim 15 , wherein the membrane comprises a plurality of pores to control the flow of the reactive vapor phase to the catalyst.

17. The apparatus of claim 16 , wherein each of the plurality of pores comprises a diameter that is dependent upon the reactive vapor phase flowing through the apparatus.

18. The apparatus of claim 16 , wherein the flow of the reactive vapor phase is dependent on a size of each of the plurality of pores.

19. The apparatus of claim 12 , wherein reactive vapor phase flowing from the first propellant tank interacts with the catalyst to produce a hot decomposition of gases.

20. The apparatus of claim 12 , wherein the reactive vapor phase flowing from the first propellant tank is due to the vacuum of space proximate to the nozzle, resulting in the pressure differential.

21. The apparatus of claim 12 , further comprising:
a second tank comprising a second propellant, the second propellant flows from the second propellant tank and is mixed with the reactive vapor phase prior interacting with the catalyst.

22. The apparatus of claim 12 , further comprising:
a thermal guard placed between the membrane and a cold chamber to maintain the reactive vapor phase in the cold chamber thermally separated from the catalyst.

23. An apparatus, comprising:
a first propellant tank comprising liquid propellant having a reactive vapor phase;
a catalyst located downstream of the first propellant tank along a vapor flow path;
a second propellant tank comprising a second propellant, wherein
the reactive vapor phase and the second propellant is mixed prior to passing through a membrane, and
the first propellant tank is configured to be selectively exposed to the pressure of space, generating a pressure differential causing a flow of vapor from the first propellant tank and through a valve, the membrane, a collection of tubes, or a combination thereof, to interact with the catalyst to generate thrust while maintaining the liquid propellant in the first propellant tank; and
a propellant management device configured to prevent the liquid propellant from escaping the first propellant tank and propagating through the apparatus.

24. An apparatus, comprising:
a first propellant tank comprising liquid propellant having a reactive vapor phase with a vapor pressure of less than 1 atmosphere at 25 degrees Celsius;
a second propellant tank comprising a second propellant, wherein
the reactive vapor phase and the second propellant is mixed prior to passing through a membrane, and
the reactive vapor phase is pulled without pulling or pushing the liquid propellant from the first propellant tank and through a valve and the membrane by way of a pressure differential, the pressure differential being generated between the vapor pressure of the propellant and space; and
a propellant management device configured to prevent the liquid propellant from escaping the propellant tank and propagating through the apparatus.

Assignees

• Aerospace Corp

Inventors

• Rhodes Brandie L

Classifications

• F02K9/68 Primary

  Decomposition chambers · CPC title

• F02K9/425

  Propellants · CPC title

• F02K9/605

  Reservoirs · CPC title

• F02K9/54

  Leakage detectors; Purging systems; Filtration systems · CPC title

• F02K9/58 Primary

  Propellant feed valves · CPC title