This paper describes a low-gravity propellant gauging system (PGS) developed, tested, and patented at Hughes Aircraft Company. The PGS predicts spacecraft end of life (EOL) within ± 2 months or better at midlife for a 15-year nominal mission and is used in the Hughes HS601 geosynchronous communications satellites. The PGS is conceptually simple and strives to minimize hardware required for implementation. It incorporates high-resolution pressure transducers and interconnect valves between existing pressurant and propellant tanks. The PGS employs periodic repressurization of propellant tanks by momentary opening of the interconnect valve between the relatively higher pressure pressurant tank and the propellant tank. Measurements of pressures before and after repressurization allow the determination of gas volume in the propellant tank through gas-law calculations, which in turn yields liquid volume, and hence propellant mass within the tank. The use of the gas law also requires temperature measurements, tor accurate temperature measurement, multiple temperature sensors are employed in each tank, and to enhance further the accuracy, extremely accurate and high-resolution pressure transducers are used as gas thermometers. Prototype testing of the proposed measurement scheme has established confidence in the system's ability to predict spacecraft EOL accurately due to propellant depletion. The PGS is failure-toler ant and does not interfere with normal operation of the propulsion subsystem. The repressurizatioh capability offers an additional advantage of closely controlling the oxidizer-to-fuel-mixture ratio in a bipropellant propulsion system. This, in turn, increases the stationkeeping life by minimizing the propellant residuals associated With depletion of one propellant species before the other.
Read full abstract