Abstract: An N-Tiered enterprise and/or N-Tiered Web-based enterprise system and methods for managing, monitoring, coordinating the procedures of and optionally controlling a fleet of geosynchronous satellites through a distributed network such as the Internet. The system and associated object oriented software architecture seamlessly supports monitoring and analyzing real-time, near real-time, historical/playback, simulated and archived satellite telemetry as well as Tracking, Telemetry and Control (TT&C) ground system generated data products such as real-time alerts, archived alerts and ground system server statuses from a group of legacy distributed TT&C wide area network (WAN) ground station systems located around the world.

Abstract: A system and method for controlling a propulsion system of a space-borne object (e.g., a satellite) is based on the principle that temperature in the propellant tank of the propulsion system is directly proportional to the pressure therein. Accordingly, when pressure drops, the system and method maintains a desired pressure in the propellant tank by heating the tank. The amount of heat to be applied is determined based on an evaluation of thruster performance data collected during satellite test maneuvers. Heating of the tank may be coupled with the introduction of helium gas to provide a two-pronged approach for maintaining tank pressure. Alternatively, the helium gas may itself be heated prior to its introduction into the propellant tank. By maintaining a desired tank pressure, efficient performance of the satellite thrusters is assured.

Abstract: A system and method for controlling a propulsion system of a space-borne object (e.g., a satellite) is based on the principle that temperature in the propellant tank of the propulsion system is directly proportional to the pressure therein. Accordingly, when pressure drops, the system and method maintains a desired pressure in the propellant tank by heating the tank. The amount of heat to be applied is determined based on an evaluation of thruster performance data collected during satellite test maneuvers. Heating of the tank may be coupled with the introduction of helium gas to provide a two-pronged approach for maintaining tank pressure. Alternatively, the helium gas may itself be heated prior to its introduction into the propellant tank. By maintaining a desired tank pressure, efficient performance of the satellite thrusters is assured.