Space-based gas supply system

Patent metadata

Field	Value
Publication number	US-11053027-B2
Application number	US-201816148870-A
Country	US
Kind code	B2
Filing date	Oct 1, 2018
Priority date	Oct 1, 2018
Publication date	Jul 6, 2021
Grant date	Jul 6, 2021

Abstract

A method of supplying a receiving tank of a receiving spacecraft with a supply gas. The method includes coupling a second end of a transfer line in flow communication with the receiving tank. The transfer line extends from a first end to the second end. The first end is coupled to a transfer tank disposed on a supply spacecraft. The transfer tank holds a transfer quantity of the supply gas. The supply spacecraft includes a heating system coupled in thermal communication with the transfer tank and a transfer valve operatively coupled to the transfer line. The method also includes activating the heating system while the transfer valve is closed such that a pressure of the transfer quantity of the supply gas is increased. The method further includes opening the transfer valve, wherein a difference between the increased pressure of the supply gas in the transfer tank and a pressure in the receiving tank causes a portion of the transfer quantity of the supply gas to flow through the transfer line to the receiving tank.

First claim

What is claimed is:

1. A method of supplying a receiving tank of a receiving spacecraft with a supply gas, said method comprising:
coupling a transfer line of a supply spacecraft in flow communication with the receiving tank on the receiving spacecraft, wherein the transfer line is coupled to a transfer tank disposed on the supply spacecraft, wherein the transfer tank holds a transfer quantity of the supply gas, wherein the supply spacecraft includes (i) a heating system coupled in thermal communication with the transfer tank and (ii) a transfer valve operatively coupled to the transfer line;
activating the heating system while the transfer valve is closed such that a pressure of the transfer quantity of the supply gas is increased; and
opening the transfer valve, wherein a difference between the increased pressure of the supply gas in the transfer tank and a pressure in the receiving tank causes a portion of the transfer quantity of the supply gas to flow through the transfer line to the receiving tank.

2. The method of claim 1 , wherein a supply line is coupled in flow communication between the transfer tank and a supply tank disposed on the supply spacecraft, wherein the supply tank holds a supply quantity of the supply gas, and wherein a supply valve is operatively coupled to the supply line, wherein the receiving spacecraft includes a receiving line in flow communication between the transfer line and the receiving tank, wherein a receiving valve is operatively coupled to the receiving line, the method further comprising:
prior to the step of activating the heating system, activating a cooling system while the transfer valve is closed, wherein the cooling system is coupled in thermal communication with the transfer tank such that a pressure of an initial quantity of supply gas in the transfer tank is decreased; and
prior to the step of activating the heating system, opening the transfer valve and the supply valve and closing the receiving valve, wherein a difference between the decreased pressure of the supply gas in the transfer tank and a pressure in the supply tank causes a portion of the supply quantity of the supply gas to flow through the supply line and the transfer line to the transfer tank.

3. The method of claim 2 , further comprising repeating the steps of activating the cooling system, opening the transfer valve and the supply valve to cause the supply gas to flow through the supply line and the transfer line to the transfer tank, activating the heating system, and opening the transfer valve to cause the supply gas to flow through the transfer line to the receiving tank.

4. The method of claim 2 , wherein the cooling system is a radiative cooling system, the method further comprising rejecting heat from the initial quantity of supply gas into space with the radiative cooling system.

5. The method of claim 1 , wherein the receiving spacecraft includes a receiving line in flow communication between the transfer line and the receiving tank, wherein a receiving valve is operatively coupled to the receiving line, wherein the transfer tank includes a variable volume element separating an interior of the transfer tank into a first variable volume and a second variable volume, the first variable volume holds the transfer quantity of the supply gas and the second variable volume is coupled in flow communication with a working gas tank by a working gas line, wherein the working gas tank holds a working gas, wherein a working gas valve is operatively coupled to the working gas line, the method further comprising opening the working gas valve, the transfer valve, and the receiving valve, wherein the working gas compresses the variable volume element and correspondingly further increases the pressure of the transfer quantity of the supply gas in the transfer tank such that a portion of the transfer quantity of the supply gas flows through the transfer line and the receiving line to the receiving tank.

6. The method of claim 5 , wherein the variable volume element is a bladder, wherein the method further comprises supplying the portion of the transfer quantity of the supply gas from the transfer tank.

7. The method of claim 5 , wherein the variable volume element is a bellows, wherein opening the working gas valve, the transfer valve, and the receiving valve comprises flowing the working gas into the second variable volume, wherein the working gas within the second variable volume compresses the bellows and correspondingly further increases the pressure of the transfer quantity of the supply gas in the transfer tank such that a portion of the transfer quantity of the supply gas flows through the transfer line and the receiving line to the receiving tank.

8. The method of claim 7 , wherein a supply line is coupled in flow communication between the transfer tank and a supply tank disposed on the supply spacecraft, wherein the supply tank holds a supply quantity of the supply gas, and wherein a supply valve is operatively coupled to the supply line, the method further comprising:
prior to the step of opening the working gas valve, venting the second variable volume and opening the transfer valve and the supply valve, such that the bellows is pushed into an expanded volume condition by a pressure in the supply tank being higher than the pressure of the transfer quantity of the supply gas in the transfer tank such that a portion of the supply quantity of the supply gas into the first variable volume.

9. The method of claim 1 , wherein a supply line is coupled in flow communication between the transfer tank and a supply tank disposed on the supply spacecraft, wherein the supply tank holds a supply quantity of the supply gas, and wherein a supply valve is operatively coupled to the supply line, the method further comprising:
closing the transfer valve such that supply gas is prevented from flowing into the transfer tank; and
opening the supply valve, wherein a difference between a pressure of the supply gas in the supply tank and a pressure in the receiving tank causes a portion of the supply quantity of the supply gas to flow through the supply line and to the receiving tank.

10. The method of claim 9 , wherein the receiving spacecraft includes a receiving line in flow communication between the transfer line and the receiving tank, wherein a receiving valve is operatively coupled to the receiving line, the method further comprising opening the receiving valve, wherein the portion of the supply quantity of the supply gas flows through the receiving line and to the receiving tank.

11. The method of claim 1 , wherein the heating system comprises an electric heating system.

12. The method of claim 1 , wherein a supply line is coupled in flow communication between the transfer tank and a supply tank disposed on the supply spacecraft, wherein the supply tank holds a supply quantity of the supply gas, and wherein a supply valve is operatively coupled to the supply line, wherein the method further comprises, prior to the step of activating the heating system, opening the transfer valve and the supply valve, wherein a difference between the decreased pressure of the supply gas in the transfer tank and a pressure in the supply tank causes a portion of the supply quantity of the supply gas to flow through the supply line and the transfer line to the transfer tank.

13. The method of claim 1 , wherein the receiving spacecraft includes a receiving line in flow communication between the transfer line and the receiving tank, wherein a receiving valve is operatively coupled to the receiving line, wherein opening the transfer valve comprises opening the transfer valve and the receiving val

Assignees

• Boeing Co

Inventors

• Behrens John
• Christy Craig Alan
• Mactavish Andrew Ian
• Nemeth Kevin

Classifications

• B67D7/36 Primary

  Arrangements of flow- or pressure-control valves (associated with nozzles B67D7/42) · CPC title

• B64G1/413

  Ion or plasma engines · CPC title

• B64G1/402 Primary

  Propellant tanks; Feeding propellants · CPC title

• B64G1/4024

  refuelling in space · CPC title

• B64G1/646

  Docking or rendezvous systems (refuelling in space B64G1/4024) · CPC title