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We present the characterization of a miniaturized ionic liquid electrospray thruster for Nanosatellite applications. The thruster investigated features an emitter array of 480 emitter tips per square centimeter and a 1 cubic centimeter propellant tank with an entirely passive propellant supply, and is operated at a power level of < 0.15W. The paper presents energy-, and mass-resolving beam spectroscopy of the packaged thruster system, as well as two independent thrust measurements. This allows to derive thruster performance parameters under realistic firing conditions, including individual thruster e ciency contributions, specific impulse and thrust. Total thruster e ciencies of 36%, specific impulse of ⇠ 760s, including all losses, and thrust of 11 12.5µN are presented, at emission currents of 150µA, for a device of ⇠ 1cm 2. Current emission data without current decay of ⇠ 90h is presented, with a maximum of 172h.

Abstract-As small satellites become more popular and capable, strategies to provide in-space propulsion increase in importance. Applications range from orbital changes and maintenance, attitude control and desaturation of reaction wheels to drag compensation and de-orbit at spacecraft end-of-life. Space propulsion can be enabled by chemical or electric means, each having different performance and scalability properties. The purpose of this review is to describe the working principles of space propulsion technologies proposed so far for small spacecraft. Given the size, mass, power and operational constraints of small satellites, not all types of propulsion can be used and very few have seen actual implementation in space. Emphasis is given in those strategies that have the potential of miniaturization to be used in all classes of vehicles, down to the popular 1-liter, 1 kg CubeSats and smaller.

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