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Fluid systems are receiving widespread usage in space vehicles. Typical applications include the use of pneumatic power for attitude control of an orbiting satellite. Selection of a pneumatic system for satellite control is predicated on certain key requirements and constraints imposed upon the system. Chief among these are thrust level, total impulse, electrical power, weight, reliability, and cost. The above parameters are considered in a case example of tradeoff studies that ultimately leads to a pneumatic system design for attitude control of a long-life orbiting satellite.