Aerodynamic study of a 3U CubeSat for drag-based in-plane orbital maneuvers in Very Low Earth Orbit

This work studies the aerodynamics of a 3U CubeSat with panels to perform drag-based in-plane orbital maneuvers in Very Low Earth Orbit (VLEO). Indeed, drag can be exploited to affect the semi-major axis, enabling relative motion. Given the rarefied atmospheric environment at these altitudes, Direct Simulation Monte Carlo (DSMC) is employed to investigate interactions between bodies and particles. The study assesses comprehensive trends in the aerodynamic coefficients for altitudes ranging from 180 km to 300 km. An aerodynamic analysis of a 3U CubeSat with four 3U panels shows pitch stability over a wide range of angles of attack (−45° to +45°). A formation with a chief and a deputy CubeSat at the same altitude is considered, with the deputy following the chief. Then, a phasing maneuver of the deputy is analyzed using the General Mission Analysis Tool (GMAT). Operational altitudes of 300 km and 400 km are examined to compare maneuver duration and orbital decay. Along-track displacements from −60 km to +60 km result in a semi-major axis decay of 2 km at 400 km and 6.4 km at 300 km. Maneuver durations are approximately 6 days at 400 km and 3 days at 300 km. This study introduces a novel approach to harnessing atmospheric drag for in-plane orbital maneuvers in VLEO, offering a fuel-free alternative for relative motion control between CubeSats. The results provide useful insights and lay groundwork for further exploration in CubeSat aerodynamics and orbital dynamics.