Abstract
T HE advantages of pulsed plasma thrusters (PPTs), constant readiness for operation and capability for precise thrust and impulse control, are well known. That is why modern PPTs are designed for spacecraft attitude control and stationkeeping systems. All these thrusters are devices of the erosion type, with an electromagnetic or electrothermal mechanism of plasma acceleration. PPT operation with liquid or gaseous propellants is in the stage of laboratory prototype development. But in some cases, it is more advisable to use gas as the propellant. One obvious example is PPTs for an attitude control system of a spacecraft where the main propulsion system is fed by gaseous propellant [comprising stationary plasma thrusters (SPT), for example].' Application of low-power PPTs, using the same gaseous propellant as the main propulsion system and powered by a common power source combined with a power processing unit (PPU), would be the best solution from the mass characteristic point of view.
Published Version
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