On the optimal passive formation reconfiguration by using attitude control

The possibility to reconfigure satellite formations with utilization of the drag and the solar radiation pressure has been established with previous works. Passive formation reconfiguration maneuvers may be achieved by controlling the attitude of the satellites and varying the area exposed to the perturbation forces. This paper deals with the development of a simple but effective model to understand the possibilities offered by this kind of maneuvers. Limits and advantages of the presented maneuvers are examined considering different reconfigurations maneuvers among close relative trajectories in Low Earth Orbits, Medium Earth Orbits and Geostationary Orbits. The theoretical investigations are confirmed by numerical simulations where the Inverse Dynamics Particle Swarm Optimization is employed. The relative dynamics is simulated with a high-fidelity orbital simulator considering all the perturbations affecting the spacecrafts orbits and the gravity gradient torque influencing the attitude dynamics. Several test cases are reported to underline all the possibilities offered by the proposed maneuvering strategy.