Characterization of a CubeSat compatible magnetically levitated thrust balance for electrospray propulsion systems

Thrust estimates from an ion Electrospray Propulsion System [1] can be inferred by measuring the electrical current consumed by the device. However, it is very challenging to directly measure the microNewton thrust these thrusters generate. A thrust balance was designed, constructed, and characterized to tackle this difficult problem and measure thrust directly. A complete electrospray power processing unit used for the thrust stand will also be described.