Multi-Objective Optimization of Six-Degree-of-Freedom Satellite Aero-Assisted Maneuvers

Abstract

An examination of aero-assisted atmospheric entry dynamics of “generic” satellites is presented rather than for space planes or trans-atmospheric vehicles, as shown by legacy and contemporary literature. Not intended to reenter the atmosphere before mission disposal operations, a generic satellite is characterized in this research by a prismatic bus structure and deployed solar panels. For all analyses, both the translation and rotation of the satellite are modeled to account for six-degree-of-freedom motion throughout the trajectory simulations. Varying the initial altitude, orbital inclination, vehicle orientation, and aerodynamic coefficients in a series of design of experiments campaigns reveals that only a limited set of initial states produce a family of results that maximize both the trans-atmospheric inclination change and the post-skip apogee altitude. Specifically, analysis indicates that a trade space exists to achieve a change in inclination as great as 2 deg at the cost of the post-skip altitude of the satellite. Alternatively, a change in inclination of approximately 0.1 deg can result in minimal altitude loss following the skip maneuver. While traditional exo-atmospheric maneuvers may deliver inclination changes greater than those presented in this research, the ability of satellites in low Earth orbit to use aero-assisted maneuvers may expand the options for altering the orientation of the orbital plane of a satellite within the contested, congested, and competitive environment of space.