PUMA
Istituto di Scienza e Tecnologie dell'Informazione     
Pardini C., Anselmo L. Influence of the spacecraft end-of-life re-orbiting altitude on the long-term collision risk in the geostationary ring. In: Advances in Space Research, vol. 28 pp. 1403 - 1408. 2001.
 
 
Abstract
(English)
A novel approach was developed to assess the contribution of satellite explosions to the object density in the geostationary ring. A low intensity explosion of a typical operational spacecraft was simulated at eight different altitudes, in between 0 and 2OCHl km above the geostationary orbit (GEO). The fragments produced were propagated for 72 years, taking into account all the relevant perturbations, and their contribution to the average object density in the GE0 ring, both short and long-term, was analyzed as a function of the end-of-life re-orbiting altitude. The explosions in geostationary orbit are the most detrimental for the GE0 ring environment. However, the average fragment density in the ring is never higher than 16 of the current background, decreasing to less than l/100 of the existent environment after 4 years, apart for the density rebound, about five decades later, due to the luni-solar perhuWions. The spacecraft end-of-life re-orbiting is a possible mitigation solution, but the long-term situation improves quite slowly, as a function of the altitude above GEO, if the explosions continue to occur. A reorbiting 300 km above the geostationary altitude seems adequate to guarantee, after 2 - 4 years, a long-term average density of fragments in the GE0 ring at least two orders of magnitude below the present-day background, even during the density rebound observed after 54 years. However, at least 1000 km of re-orbiting are needed to stay below that l/100 threshold also in the short-term
Subject Satellite
Spacecraft
J.2 Physical Sciences and Engineering


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