Minimum-Time reconfiguration maneuvers of satellite formations using perturbation forces

A novel approach for minimum-time reconfiguration of satellite formations is proposed considering the perturbation forces as control variables. Planning appropriate attitude maneuvers for each satellite, the atmospheric drag and of the solar radiation pressure are properly controlled, and the formation is given the appropriate inputs to achieve the imposed reconfiguration. Limits and advantages of the presented maneuvers are examined considering low Earth orbits, medium Earth orbits, and geostationary orbits. The recent inverse dynamics particle swarm optimization is involved; the integration of the attitude dynamics is avoided, thus reducing the computational effort, and satisfied attitude constraints at the initial and final time instants are guaranteed. B-spline curves approximate the attitude kinematics, variable time mesh points are introduced, and adaptive decreasing tolerances are considered for the imposed constraints. The evolution of the configuration is simulated with a high-fidelity orbital simulator considering all the perturbations that can affect the maneuver. Two test cases are taken into account, one involving a circular formation reconfiguration and the other an along-track reconfiguration.