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.
