Ionospheric Drag for Satellite Formation Control

Abstract

Constellations of miniaturized satellites that provide novel and cost-effective capabilities are a growing trend for space systems. Economically viable miniature satellite constellations commonly necessitate the exclusion of propulsion systems. A difference in neutral aerodynamic forces between spacecraft, resulting from interactions with the thermosphere, is the prevailing propulsion-free method for maintaining low-Earth-orbit constellations. This work investigates charged aerodynamic forces, which are caused by an electrically charged platform’s interaction with the ionosphere (ionospheric drag), as an actuation mechanism for satellite formation control. Numerical propagations of the relative motion between identically shaped neutral and charged spheres, with artificial surface voltages ranging between and V, indicate that the ensuing magnitude of differential drag, due to ionospheric drag, can nullify an initial 1 m relative semimajor axis within 4 min in the most optimal conditions simulated. Thus, with no technology optimization, this work concludes that ionospheric drag caused by spacecraft charging is sufficient for actuating changes in the orbital semimajor axis; however, it is inferior when compared to techniques for generating differences in neutral drag. Future work will investigate the optimization of ionospheric aerodynamic technologies and techniques to increase the effectiveness of charged aerodynamic formation control.