A passive satellite deorbiting strategy for medium earth orbit using solar radiation pressure and the J2 effect

The growing population of space debris poses a serious risk to the future of space flight. To effectively manage the increase of debris in orbit, end-of life disposal has become a key requirement for future missions. This poses a challenge for Medium Earth Orbit (MEO) spacecraft which require a large Δv to re-enter the atmosphere or reach the geostationary graveyard orbit. This paper further explores a passive strategy based on the joint effects of solar radiation pressure and the Earth's oblateness acting on a high area-to-mass-ratio object. The concept was previously presented as an analytical planar model. This paper uses a full 3D model to validate the analytical results numerically for equatorial circular orbits first, then investigating higher inclinations. It is shown that for higher inclinations the initial position of the Sun and right ascension of the ascending node become increasingly important. A region of very low required area-to-mass-ratio is identified in the parameter space of semi-major axis and inclination which occurs for altitudes below 10,000 km.

► SRP-augmented deorbiting uses solar radiation pressure to passively deorbit.
► The required area-to-mass-ratio to deorbit from MEO is calculated analytically.
► The results are verified numerically.
► The numerical model is then used to analyse inclined and eccentric orbits.
► MEO regimes are identified in which SRP-augmented deorbiting is most effective.