  Recent works demonstrated that the dynamics caused by the planetary
oblateness coupled with the solar radiation pressure can be described through a
model based on singly-averaged equations of motion. The coupled perturbations
affect the evolution of the eccentricity, inclination and orientation of the
orbit with respect to the Sun--Earth line. Resonant interactions lead to
non-trivial orbital evolution that can be exploited in mission design.
Moreover, the dynamics in the vicinity of each resonance can be analytically
described by a resonant model that provides the location of the central and
hyperbolic invariant manifolds which drive the phase space evolution. The
classical tools of the dynamical systems theory can be applied to perform a
preliminary mission analysis for practical applications. On this basis, in this
work we provide a detailed derivation of the resonant dynamics, also in
non-singular variables, and discuss its properties, by studying the main
bifurcation phenomena associated to each resonance. Last, the analytical model
will provide a simple analytical expression to obtain the area-to-mass ratio
required for a satellite to deorbit from a given altitude in a feasible
timescale.
