Symplectic integrators for the simulation of space debris evolution

Paper number

IAC-17,A6,IP,6,x39076

Author

Dr. Pierfrancesco Di Cintio, CNR, Italy

Coauthor

Dr. Alessandro Rossi, IFAC-CNR, Italy

Coauthor

Dr. Giovanni B. Valsecchi, Institute for Space Astrophysics and Planetology (IAPS), Italy

Year

2017

Abstract

In the study of the long term evolution of the space debris population
it is of paramount importance to be able to achieve a good compromise
between accuracy and computational speed, in order to propagate the
orbit of thousands of objects at the same time.

We present a novel implementation of a symplectic orbital propagator
in Cartesian coordinates for the dynamics of space debris from the Low to
High Earth orbit range.

Test simulations including luni-solar perturbations suggest that our optimized
numerical code can attain a significant reduction in computational times with
respect to previous orbit propagators based on averaged dynamics in orbital
elements.

Moreover, we show preliminarily results for case studies where the
effects of non-gravitational perturbations such as solar radiation
pressure and atmospheric drag, often not accounted for in
symplectic integrators, are considered.

Finally, the comparison between the results of a few long term evolution
scenarios simulated with the SDM model, using both the original propagator
(working on averaged dynamics in orbital elements) and the new one, are presented.

Abstract document

IAC-17,A6,IP,6,x39076.brief.pdf

Manuscript document

IAC-17,A6,IP,6,x39076.pdf (🔒 authorized access only).

To get the manuscript, please contact IAF Secretariat.