초록 ▼

A method for operating a satellite (10, 34) so that a predetermined amount of propellant is left to perform end-of-life maneuvers is provided. A first pressure differential is established between a first propellant tank (74) and a second propellant tank (76) by pressurizing the first tank (76) with

A method for operating a satellite (10, 34) so that a predetermined amount of propellant is left to perform end-of-life maneuvers is provided. A first pressure differential is established between a first propellant tank (74) and a second propellant tank (76) by pressurizing the first tank (76) with a pressurant. Propellant is transferred from the first tank (74) to the second tank (76). Using precise control during transfer the amount of propellant in the tanks may be determined. The second tank is used for orbit maintenance. The first tank is used for end-of-life maneuvers. Propellant may be transferred between the tanks using a latching process so that a predetermined amount of propellant may be transferred from a non-empty tank to a full tank.

대표청구항 ▼

The invention claimed is: 1. A method for operating a satellite comprising: pressurizing a first tank with a pressurant thereby establishing a pressure differential between a first propellant tank and a second propellant tank; transferring propellant from a first tank to a second tank; using prope

The invention claimed is: 1. A method for operating a satellite comprising: pressurizing a first tank with a pressurant thereby establishing a pressure differential between a first propellant tank and a second propellant tank; transferring propellant from a first tank to a second tank; using propellant in the second tank for orbit maintenance; and using propellant in the first tank for end-of-life maneuvers. 2. A method as recited in claim 1 wherein establishing a pressure differential comprises heating the second tank. 3. A method as recited in claim 1 further comprising after the step of transferring, burning to depletion propellant in the first tank and transferring propellant from the second tank to the first tank. 4. A method as recited in claim 3 further comprising after the step of burning, venting the first tank. 5. A method as recited in claim 3 wherein transferring propellant from the second tank to the first tank comprises equalizing pressure between the first tank and the second tank. 6. A method as recited in claim 5 wherein equalizing pressure comprises opening latch valves for a predetermined amount of time. 7. A method as recited in claim 1 wherein establishing a pressure differential comprises expelling helium from the first tank. 8. A method as recited in claim 1 wherein establishing a pressure differential comprises opening at least one valve between a pressurant and the first tank. 9. A method as recited in claim 1 wherein transferring propellant comprises transferring a known amount. 10. A method as recited in claim 9 wherein transferring a known amount comprises opening latch valves for a predetermined amount of time. 11. A method as recited in claim 1 wherein the first propellant in the first tank is the same as the propellant in the second tank. 12. A method as recited in claim 1 wherein the satellite comprises a three axis satellite. 13. A method as recited in claim 1 wherein the satellite comprises a spinning satellite. 14. A method as recited in claim 1 wherein using the propellant in the second tank comprises measuring the amount of propellant used in the second tank until the second tank is emptied to determine the amount in the first tank. 15. A method as recited in claim 14 further comprising after using the propellant in the second tank, transferring a portion of the propellant from the first tank to the second tank. 16. A method as recited in claim 1 further comprising maintaining a nominal tank pressure in the first tank. 17. A method as recited in claim 1 further comprising maintaining a nominal tank pressure in the second tank. 18. A method as recited in claim 1 further comprising maintaining a nominal tank pressure to maintain thruster performance. 19. A method as recited in claim 1 further comprising determining a first amount of propellant in the first tank and a second amount of propellant in the second tank. 20. A method as recited in claim 19 determining a first amount of propellant in the first tank and a second amount of propellant in the second tank comprises using modeling. 21. A method for operating a satellite having a first propellant tank and a second propellant tank comprising: opening a valve between a pressurant source and a first tank; pressurizing a first tank from the pressurant source; establishing a pressure differential between a first propellant tank and a second propellant tank; closing the valve; transferring propellant from the first tank to the second tank by controlling valves therebetween; using propellant in the second tank for orbit maintenance; and using propellant in the first tank for end-of-life maneuvers. 22. A method as recited in claim 21 further comprising after the step of transferring, burning to depletion propellant in the first tank and transferring propellant from the second tank to the first tank. 23. A method as recited in claim 22 further comprising after the step of burning, venting the first tank. 24. A method as recited in claim 22 wherein transferring propellant from the second tank to the first tank comprises equalizing pressure between the first tank and the second tank. 25. A method as recited in claim 24 wherein equalizing pressure comprises opening latch valves for a predetermined amount of time. 26. A method as recited in claim 21 further comprising maintaining a nominal tank pressure in the first and second tank to maintain thruster performance. 27. A method as recited in claim 21 further comprising determining a first amount of propellant in the first tank and a second amount of propellant in the second tank. 28. A method as recited in claim 27 determining a first amount of propellant in the first tank and a second amount of propellant in the second tank comprises using modeling.