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As part of the dynamical analysis carried out within the Horizon 2020ReDSHIFT project, this work analyzes the possible strategies to guide lowaltitude satellites towards an atmospheric reentry through an impulsivemaneuver. We consider a fine grid of initial conditions in semi-major axis,eccentricity and inclination and we identify the orbits that can be compliantwith the 25-year rule as the target of a single-burn strategy. Besides theatmospheric drag, we look for the aid provided by other dynamical perturbations- mainly solar radiation pressure - to facilitate a reentry. Indeed, in thecase of typical area-to-mass ratios for objects in LEO, we observed thatdynamical resonances can be considered only in combination with the atmosphericdrag and for a very limited set of initial orbits. Instead, if an areaaugmentation device, as a solar sail, is available on-board the spacecraft, weverified that a wider range of disposal solutions become available. Thisinformation is exploited to design an improved mitigation scheme, that can beapplied to any satellite in LEO.

Exploiting dynamical perturbations for the end-of-life disposal of spacecraft in LEO