On-orbit propellant metering and refueling
A first spacecraft includes a first fluid storage arrangement and a fluid flow metering arrangement including a holding tank coupled with the first fluid storage arrangement, a flow meter disposed proximate to the holding tank, and an active thermal control arrangement controlling the temperature of the flow meter and the holding tank. The first spacecraft is configured to service a second spacecraft, the second spacecraft including a second fluid storage arrangement, by transferring one or both of a propellant and a pressurant from the first fluid storage arrangement to the holding tank, and from the holding tank, through the flow meter, to the second fluid storage arrangement.
1. A system comprising:
a first spacecraft including:
a first fluid storage arrangement; and
a fluid flow metering arrangement, the fluid flow metering arrangement including:
a holding tank coupled with the first fluid storage arrangement,
a flow meter disposed proximate to the holding tank, and
an active thermal control arrangement; wherein
the first spacecraft is configured to service a second spacecraft, the second spacecraft including a second fluid storage arrangement, by transferring one or both of a propellant and a pressurant from the first fluid storage arrangement to the holding tank, and from the holding tank, through the flow meter, to the second fluid storage arrangement; and
at least during the transferring of the one or both of the propellant and the pressurant, the active thermal control arrangement maintains a temperature of the flow meter and the holding tank within a specified range.
2. The system of claim 1 , wherein the first fluid storage arrangement includes at least one liquid propellant tank and at least one pressurant tank and the holding tank is selectably coupled with one or both of the liquid propellant tank and the pressurant tank.
3. The system of claim 1 , wherein the active thermal control arrangement includes an isothermal mounting panel, one or more heat pipes and a thermostatically controlled heater.
4. The system of claim 1 , wherein the first spacecraft includes a pressurant tank and a plurality of regulator modules are disposed in parallel between the pressurant tank and the holding tank, each regulator module including a pressure regulator and a control valve.
5. The system of claim 4 , wherein the regulator modules are configured to deliver pressurant from the pressurant tank to the holding tank at a selectable regulated pressure.
6. The system of claim 4 , wherein the plurality of regulator modules are includes one or both of an analog pressure regulator and a Bang-Bang pressure regulator.
7. The system of claim 1 , wherein a measurement error of the flow meter, when temperature controlled within the specified range, is not greater than 1%.
8. The system of claim 1 , wherein the active thermal control arrangement includes one or more thermoelectric coolers.
9. The system of claim 1 , wherein the first spacecraft is configured to be serviced by a third spacecraft, the third spacecraft including a third fluid storage arrangement, by transferring one or both of a propellant and a pressurant from the third fluid storage arrangement to the holding tank, and from the holding tank, through the flow meter, to the first fluid storage arrangement.
10. A method comprising:
operating a first orbiting spacecraft, the first spacecraft including a first fluid storage arrangement, a flow meter, a holding tank disposed proximate to the flow meter and an active thermal control arrangement;
transferring one or both of a propellant and a pressurant from the holding tank, through the flow meter, to a second fluid storage arrangement; and
maintaining, at least during the transferring, with the active thermal control arrangement, a temperature of the flow meter and the holding tank within a specified range.
11. The method of claim 10 , wherein the first fluid storage arrangement includes at least one liquid propellant tank and at least one pressurant tank and the holding tank is selectably coupled with one or both of the liquid propellant tank and the pressurant tank.
12. The method of claim 10 , wherein the active thermal control arrangement includes an isothermal mounting panel, one or more heat pipes and a thermostatically controlled heater.
13. The method of claim 10 , wherein a measurement error of the flow meter, when temperature controlled within the specified range is not greater than 1%.
14. The method of claim 10 , further comprising servicing a second orbiting spacecraft, the second spacecraft including the second fluid storage arrangement.
15. The method of claim 14 , further comprising receiving service from a third orbiting spacecraft, the third spacecraft including a third fluid storage arrangement, the service including transferring one or both of a propellant and a pressurant from the third fluid storage arrangement to the holding tank, and from the holding tank, through the flow meter, to the first fluid storage arrangement.
16. A method comprising:
operating a first orbiting spacecraft, the first spacecraft including a first fluid storage arrangement, a flow meter, a holding tank disposed proximate to the flow meter and an active thermal control arrangement;
servicing a second orbiting spacecraft, the second spacecraft including a second fluid storage arrangement, by transferring one or both of a propellant and a pressurant from the holding tank, through the flow meter, to the second fluid storage arrangement; and
maintaining, at least during the transferring, with the active thermal control arrangement, a temperature of the flow meter and the holding tank within a specified range.
17. The method of claim 16 , wherein the first fluid storage arrangement includes at least one liquid propellant tank and at least one pressurant tank and the holding tank is selectably coupled with one or both of the liquid propellant tank and the pressurant tank.
18. The method of claim 16 , wherein the active thermal control arrangement includes an isothermal mounting panel, one or more heat pipes and a thermostatically controlled heater.
19. The method of claim 16 , further comprising receiving service from a third orbiting spacecraft, the third spacecraft including a third fluid storage arrangement, the service including transferring one or both of a propellant and a pressurant from the third fluid storage arrangement to the holding tank, and from the holding tank, through the flow meter, to the first fluid storage arrangement.
20. The method of claim 16 , wherein a plurality of regulator modules and control valves are disposed in parallel between the first fluid storage arrangement and the holding tank, the regulator modules and control valves configured to deliver pressurant at a selectable regulated pressure.