Celestial Mechanics and Dynamical Astronomy

, Volume 97, Issue 4, pp 289–304

Orbit determination of space debris: admissible regions

Original Article

DOI: 10.1007/s10569-007-9065-x

Cite this article as:
Tommei, G., Milani, A. & Rossi, A. Celestial Mech Dyn Astr (2007) 97: 289. doi:10.1007/s10569-007-9065-x


The main problem in the orbit determination of the space debris population orbiting our planet is identifying which separate sets of data belong to the same physical object. The observations of a given object during a passage above an observing station are collectively called a Too Short Arc (TSA): data from a TSA cannot allow for a complete determination of an orbit. Therefore, we have to solve first the identification problem, finding two or more TSAs belonging to the same physical object and an orbit fitting all the observations. This problem is well known for the determination of orbits of asteroids: we shall show how to apply the methods developed for preliminary orbit determination of heliocentric objects to geocentric objects. We shall focus on the definition of an admissible region for space debris, both in the case of optical observations and radar observations; then we shall outline a strategy to perform a full orbit determination.


Space debris Orbit determination Admissible region 

Copyright information

© Springer Science+Business Media B.V. 2007

Authors and Affiliations

  1. 1.Department of MathematicsUniversity of PisaPisaItaly
  2. 2.ISTI/CNRResearch Area of PisaPisaItaly

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