Enhanced algorithms to ensure the success of rendezvous maneuvers using aerodynamic forces

Abstract A common practice in the field of differential lift and drag controlled satellite formation flight is to analytically design maneuver trajectories using linearized relative motion models constant density assumption. However, state-of-the-art algorithms inevitably fail if initial condition final control phase exceeds an orbit spacecraft-dependent range, so-called feasibility range. This article presents enhanced for third (and final) which ensure overall success independent conditions. Thereby, all maneuvers have previously been categorized as infeasible due algorithm limitations are rendered feasible. An individual presented both possible options phase, namely or drag. In addition, a methodology precisely determine range without need computational expensive Monte Carlo simulations presented. allows fast precise assessments influences boundary conditions, such orbital inclination altitude, on