Collision Risk Mitigation in Geostationary Orbit

@article{Anselmo2000CollisionRM,
  title={Collision Risk Mitigation in Geostationary Orbit},
  author={Luciano Anselmo and Carmen Pardini},
  journal={Space Debris},
  year={2000},
  volume={2},
  pages={67-82}
}
The short- and long-term effects of spacecraft explosions, as a function of the end-of-life re-orbit altitude above the geostationary orbit (GEO), were analyzed in terms of their additional contribution to the debris flux in the GEO ring. The simulated debris clouds were propagated for 72 yrs, taking into account all the relevant orbital perturbations.The results obtained show that 6–7 additional explosions in GEO would be sufficient, in the long term, to double the current collision risk with… 
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References

SHOWING 1-8 OF 8 REFERENCES
The effectiveness of end-of-life re-orbiting for debris mitigation in geostationary orbit
The effect of satellite breakups over 72 years, as a function of the end-of-life re-orbiting altitude (0–2000 km), was analyzed in terms of fragment contribution to the object density in the
The probability of collisions on the geostationary ring
Geostationary satellites not removed from the geosynchronous altitude at the end of their useful life will expose future spacecraft orbiting in this unique region to a continual collision hazard. The
Disposal of Spacecraft at End of Life in Geosynchronous Orbit
A number of national and international organizations have adopted a policy of removing spacecraft at the end of life from the geosynchronous ring. However, a resolution of several technical issues
A New Orbital Debris Reference Model
This paper presents a new orbital debris environment model (CODRM-97). It includes the objects with a mass ≥ 1 mg produced by international space launches and operations, 140 energetic breakups and
DORIS radar calibration method
Following the interest expressed by ESA and FGAN, it was decided to realise some evaluation of the DORIS calibration method with the TIRA radar. This paper, organised in four parts, describes : the