Low-thrust de-orbiting from Low Earth Orbit through natural perturbations

This paper investigates two strategies that exploit low-thrust propulsion and natural effects for the complete de-orbiting of spacecraft from a Low Earth Orbit (LEO). The first strategy aims to actively lower perigee altitude by achieve passive drag-induced re-entry. second move reach specific condition can provoke orbital decay means coupled effect perturbations. For each strategy, sub-time-optimal closed-loop steering law, which is proved be stable, designed with Lyapunov method. Then set maps show costs LEO (i.e., Δv-budget time) are plotted as function initial conditions strategies. In this way, feasible apply identified comparing Δv-budget. Before plotting maps, averaged motion derived, reduce computational load propagation motion.