LEO Mapping for Passive Dynamical Disposal

The growth of the number of space objects in the Low Earth Orbit (LEO) region requires both the implementation of prevention strategies and the outline of advanced re-entry solutions. By means of a dedicated orbit propagator, we studied the dynamics of sample objects over 120 years, in a dense grid of orbital elements covering the whole LEO phase space, considering two initial epochs. Beyond the standard area-to-mass ratio of typical payloads in LEO, we also assumed the use of area augmentation devices. The final goal of this analysis is to take advantage of the dynamical instabilities induced by orbital perturbations to reduce the residual lifetime of disposed spacecraft. The output of the simulations highlighted that the orbital perturbations due to geopotential, lunisolar perturbations and solar radiation pressure can significantly change the eccentricity of the orbit at selected inclinations bands. A Fourier transform analysis confirmed the role of given resonances in the eccentricity evolution as a function of the initial orbital elements. An impulsive strategy to move the spacecraft at end-of-life towards the unstable zones is also sketched.