A method and system for pacing a vehicle along a path of travel is described. The method includes determining a geographical location of the vehicle, displaying a vehicle position icon representative of the geographical location, determining an optimal position for the vehicle, displaying a pace ico
A method and system for pacing a vehicle along a path of travel is described. The method includes determining a geographical location of the vehicle, displaying a vehicle position icon representative of the geographical location, determining an optimal position for the vehicle, displaying a pace icon representative of the optimal position for the vehicle, and operating the vehicle to maintain a vehicle position icon displayed on the operator pace display substantially coincident with the pace icon displayed on the operator pace display. The system includes at least one on-board tracking system configured to determine a geographical location of the vehicle, at least one on-board computer configured to determine a display position of a pace icon, and at least one on-board operator pace display configured to display the pace icon at a position determined by the on-board computer, the operator pace display further configured to display the vehicle position, as determined by the on-board computer, relative to the pace icon.
대표청구항▼
A method and system for pacing a vehicle along a path of travel is described. The method includes determining a geographical location of the vehicle, displaying a vehicle position icon representative of the geographical location, determining an optimal position for the vehicle, displaying a pace ico
A method and system for pacing a vehicle along a path of travel is described. The method includes determining a geographical location of the vehicle, displaying a vehicle position icon representative of the geographical location, determining an optimal position for the vehicle, displaying a pace icon representative of the optimal position for the vehicle, and operating the vehicle to maintain a vehicle position icon displayed on the operator pace display substantially coincident with the pace icon displayed on the operator pace display. The system includes at least one on-board tracking system configured to determine a geographical location of the vehicle, at least one on-board computer configured to determine a display position of a pace icon, and at least one on-board operator pace display configured to display the pace icon at a position determined by the on-board computer, the operator pace display further configured to display the vehicle position, as determined by the on-board computer, relative to the pace icon. nerate a first propellant mass and a second propellant mass and process the second information to generate a third propellant mass and a fourth propellant mass. 9. The system of claim 8 wherein the mixture ratio logic is configured to process the first propellant mass and the second propellant mass to generate a first difference error representative of a difference in the first propellant amount and the second propellant amount relative to a depletion rate of the first propellant and the second propellant. 10. The system of claim 9 wherein the mixture ratio logic is configured to process the third propellant mass and the fourth propellant mass to generate a second difference error representative of a difference in the third propellant amount and the fourth propellant amount relative to a depletion rate of the third propellant and the fourth propellant. 11. The system of claim 10 wherein the mixture ratio logic is configured to use the first difference error to calculate the first mixture ratio and the second difference error to calculate the second mixture ratio. 12. The system of claim 1 wherein the first thrust source is a first rocket engine and the second thrust source is a second rocket engine. 13. The system of claim 12 wherein the first and second rocket engines are bi-propellant rocket engines. 14. The system of claim 3 wherein the first and third propellant source are liquid fuel propellant sources. 15. The system of claim 3 wherein the second and fourth propellant sources are oxidizer propellant sources. 16. The system of claim 1 wherein the space vehicle is a launch vehicle. 17. A software product for a propellant utilization system in a space vehicle having at least a first thrust source and a second thrust source, the software product comprising: sequencer logic instructions operational when executed on a processor to direct the processor to determine an active one of the first and second thrust source and provide first flight parameters for the active one of the first and second thrust source; propellant logic instructions operational when executed on the processor to direct the processor to process, using the first flight parameters, first information from a first and second propellant source connected to the active one of the first and second thrust source, to determine a first propellant amount and a second propellant amount; mixture ratio logic instructions operational when executed on the processor to direct the processor to generate a first mixture ratio for the active one of the first and the second thrust source based on the first propellant amount, the second propellant amount, and the first flight parameters; and a storage medium operational to store the sequencer logic instructions, the propellant logic instructions, and the mixture ratio logic instructions. 18. The product of claim 17 wherein the sequencer logic instructions are operational to direct the processor to determine when the other one of the first and second thrust source becomes the active thrust source, and provide second flight parameters for the other one of the first and second thrust source. 19. The product of claim 18 wherein the propellant logic instructions are operational to direct the processor to process, using the second flight parameters, second information from third and fourth propellant sources connected to the other one of the first and second thrust source to determine a third propellant amount and a fourth propellant amount. 20. The product of claim 19 wherein the mixture ratio logic instructions are operational to direct the processor to generate a second mixture ratio for the other one of the first and second thrust source based on the third propellant amount, the fourth propellant amount, and the second flight parameters. 21. The product of claim 20 wherein the first mixture ratio substantially simultaneously depletes the first and second propellant sources and the second mixture ratio substantially simultaneo usly depletes the third and fourth propellant sources. 22. The product of claim 20 wherein the first mixture ratio depletes one of the first and second propellant sources before the other one of the first and second propellant sources, and the second mixture ratio depletes one of the third and fourth propellant sources before the other one of the third and fourth propellant sources. 23. The product of claim 20 wherein the first information from the first and second propellant sources comprises: a first propellant pressure information and a second propellant pressure information, and wherein the second information from the third and fourth propellant sources comprises a third propellant pressure information and a fourth propellant pressure information. 24. The product of claim 23 wherein the propellant logic instructions are operational to direct the processor to process the first information to generate a first propellant mass and a second propellant mass and process the second information to generate a third propellant mass and a fourth propellant mass. 25. The product of claim 24 wherein the mixture ratio logic instructions are operational to direct the processor to process the first propellant mass and the second propellant mass to generate a first difference error representative of a difference in the first propellant amount and the second propellant amount relative to a depletion rate of the first propellant and the second propellant. 26. The product of claim 25 wherein the mixture ratio logic instructions are operational to direct the processor to process the third propellant mass and the fourth propellant mass to generate a second difference error representative of a difference in the third propellant amount and the fourth propellant amount relative to a depletion rate of the third propellant and the fourth propellant. 27. The product of claim 26 wherein the mixture ratio logic instructions are operational to direct the processor to use first difference error to calculate the first mixture ratio and the second difference error to calculate the second mixture ratio. 28. The product of claim 17 wherein the first thrust source is a first rocket engine and the second thrust source is a second rocket engine. 29. The product of claim 28 wherein the first and second rocket engines are bi-propellant rocket engines. 30. The product of claim 17 wherein the first and third propellant source are liquid fuel propellant sources. 31. The product of claim 19 wherein the second and fourth propellant sources are oxidizer fuel propellant sources. 32. The product of claim 19 wherein the space vehicle is a launch vehicle. 33. A method for generating a mixture ratio for a space vehicle having at least a first thrust source and a second thrust source, the method comprising: determining an active thrust source, wherein the active thrust source is an active one of the first thrust source and the second thrust source; providing first flight parameters for the active thrust source; computing, using the first flight parameters, a first propellant amount in a first propellant source and a second propellant amount in a second propellant source, wherein the first and second propellant source are connected to the active thrust source; and computing, using the first flight parameters, a first mixture ratio for the active thrust source. 34. The method of claim 33 the method comprising: determining that the other one of the first thrust source and the second thrust source is the active thrust source; providing second flight parameters for the other one of the first thrust source and the second thrust source; computing, using the second flight parameters, a third propellant amount in a third propellant source and a fourth propellant amount in a fourth propellant source, wherein the third and fourth propellant sources are connected to the other one of the first and second thrust source; and computing, using the second flight parameters, a second mixture ratio for the other one of the first and second thrust source. 35. The method of claim 33 wherein the step of computing the amount of propellant in the first propellant source and the second propellant source comprises: receiving first and second propellant pressure information from the first and second propellant source; and converting the first and second propellant pressure information into first and second propellant mass information, using the first flight parameters. 36. The method of claim 35 wherein the step of computing the amount of propellant in the third propellant source and the fourth propellant source comprises: receiving third and fourth propellant pressure information from the third and fourth propellant source; and converting the third and fourth propellant pressure information into third and fourth propellant mass information, using the second flight parameters. 37. The method of claim 34 wherein the first mixture ratio substantially simultaneously depletes the first and second propellant sources and the second mixture ratio substantially simultaneously depletes the third and fourth propellant sources. 38. The method of claim 34 wherein the first mixture ratio depletes one of the first and second propellant sources before the other one of the first and second propellant sources, and the second mixture ratio depletes one of the third and fourth propellant sources before the other one of the third and fourth propellant sources. 39. The method of claim 36 comprising: computing, using the first flight parameters, a first difference error using the first and second propellant mass information representative of a difference in the first propellant amount and the second propellant amount relative to a depletion rate of the first propellant and the second propellant. 40. The method of claim 39 comprising: computing, using the second flight parameters, a second difference error using the third and fourth propellant mass information representative of a difference in the third propellant amount and the fourth propellant amount relative to a depletion rate of the third propellant and the fourth propellant. 41. The method of claim 40 comprising: computing the first mixture ratio using the first difference error; and computing the second mixture ratio using the second difference error. 42. The method of claim 33 wherein the first thrust source is a first rocket engine and the second thrust source is a second rocket engine. 43. The method of claim 42 wherein the first and second rocket engines are bi-propellant rocket engines. 44. The method of claim 34 wherein the first and third propellant source are liquid fuel propellant sources. 45. The method of claim 34 wherein the second and fourth propellant sources are oxidizer propellant sources.
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