Rigorous global optimization for collision risk assessment on perturbed orbits

  1. Morselli, A. 3
  2. Armellin, R. 1
  3. Di Lizia, P. 2
  4. Bernelli-Zazzera, F. 2
  1. 1 Universidad de La Rioja
    info

    Universidad de La Rioja

    Logroño, España

    ROR https://ror.org/0553yr311

  2. 2 Polytechnic University of Milan
    info

    Polytechnic University of Milan

    Milán, Italia

    ROR https://ror.org/01nffqt88

  3. 3 European Space Agency, European Space Operations Centre, Robert-Bosch-Straße 5, Darmstadt, Germany
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Journal:
Springer Optimization and Its Applications

ISSN: 1931-6828

Year of publication: 2016

Volume: 114

Pages: 237-267

Type: Article

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DOI: 10.1007/978-3-319-41508-6_9 SCOPUS: 2-s2.0-85008330502 GOOGLE SCHOLAR

More publications in: Springer Optimization and Its Applications

Abstract

In this chapter, a method to assess the occurrence of impacts between objects (either spacecraft or space debris) orbiting around the Earth is presented. The method is based on the computation of the minimum distance between two evolving orbits by means of a rigorous global optimizer. Analytical solutions of artificial satellite motion are utilized to account for perturbative effects of Earth’s zonal harmonics, atmospheric drag, and third body. It is shown that the method can effectively compute the intersection between perturbed orbits and hence identify pairs of space objects on potentially colliding orbits. Test cases considering sunsynchronous, low perigee and earth-synchronous orbits are presented to assess the performances of the method. © Springer International Publishing Switzerland 2016.