Patent ID: 6631314
Filing Date: 2003-10-07
Classification: B64G,F02K

Abstract:
A propellant utilization system for a space vehicle having at least a first thrust source and a second thrust source, the propellant utilization system comprising:a processing system including sequencer logic 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 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 in the first propellant source and a second propellant amount in the second propellant source; and mixture ratio logic to generate a first mixture ratio for the active one of the first and second thrust source based on the first propellant amount, the second propellant amount, and the first flight parameters.