Controller Method for Using Digital Micromirror Devices for Satellite Attitude Trim

This paper presents a novel approach to spacecraft attitude control by leveraging Digital Micromirror Devices to modulate solar radiation pressure for providing continuous torque trim. Building on prior work that presents Digital Micromirror Devices for providing highly discrete, propellant-free attitude control, this paper will further advance the concept by applying Digital Micromirror Device-based solar trim control to geosynchronous satellites. It will first compare the method to existing solar trim tab control and then apply it to a notional geosynchronous satellite example.