Abstract: A cryogenic propellant depletion system for maximizing cryogenic propellant use in a space launch vehicle. The cryogenic propellant depletion system utilizes a plurality of pressure measurements to monitor one or more parameters of the cryogenic propellant in a feed line interconnecting a cryogenic propellant storage tank to the launch vehicle's engine. In this regard, the cryogenic depletion system includes a processor and supported logic to determine a head pressure supplied by the cryogenic propellant in the feed line and the mass of the cryogenic propellant in the feed line. The cryogenic depletion monitoring system is operative to determine these propellant parameters irrespective of a two-phase flow existing in the feed line. Finally, the system is configured to initiate engine shut down when at least one of the determined propellant parameters falls below a minimum threshold value.

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 utilizes a common set of algorithms to generate mixture ratios for each thrust source as each thrust source becomes active. The propellant utilization system includes a processing system comprising sequencer logic, propellant logic, and mixture ratio logic. The sequencer logic determines when a thrust source is active, e.g. one of the first and second thrust sources, and provides flight parameters for the active thrust source to the propellant logic and the mixture ratio logic. The propellant logic processes information from propellant sources connected to the active thrust source, using the flight parameters for that thrust source, to determine an amount of remaining propellant in each source.

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 utilizes a common set of algorithms to generate mixture ratios for each thrust source as each thrust source becomes active. The propellant utilization system includes a processing system comprising sequencer logic, propellant logic, and mixture ratio logic. The sequencer logic determines when a thrust source is active, e.g. one of the first and second thrust sources, and provides flight parameters for the active thrust source to the propellant logic and the mixture ratio logic. The propellant logic processes information from propellant sources connected to the active thrust source, using the flight parameters for that thrust source, to determine an amount of remaining propellant in each source.

Abstract: A cryogenic propellant depletion system for maximizing cryogenic propellant use in a space launch vehicle. The cryogenic propellant depletion system utilizes a plurality of pressure measurements to monitor one or more parameters of the cryogenic propellant in a feed line interconnecting a cryogenic propellant storage tank to the launch vehicle's engine. In this regard, the cryogenic depletion system includes a processor and supported logic to determine a head pressure supplied by the cryogenic propellant in the feed line and the mass of the cryogenic propellant in the feed line. The cryogenic depletion monitoring system is operative to determine these propellant parameters irrespective of a two-phase flow existing in the feed line. Finally, the system is configured to initiate engine shut down when at least one of the determined propellant parameters falls below a minimum threshold value.