End-of-life Earth re-entry for highly elliptical orbits: the INTEGRAL mission (Contributo in atti di convegno)

Type
Label
  • End-of-life Earth re-entry for highly elliptical orbits: the INTEGRAL mission (Contributo in atti di convegno) (literal)
Anno
  • 2014-01-01T00:00:00+01:00 (literal)
Alternative label
  • C. Colombo, F. Letizia, E.M. Alessi, M. Landgraf (2014)
    End-of-life Earth re-entry for highly elliptical orbits: the INTEGRAL mission
    in AAS/AIAA Space Flight Mechanics Meeting, Santa Fe, New Mexico, U.S.A., 26-30 gennaio 2014
    (literal)
Http://www.cnr.it/ontology/cnr/pubblicazioni.owl#autori
  • C. Colombo, F. Letizia, E.M. Alessi, M. Landgraf (literal)
Http://www.cnr.it/ontology/cnr/pubblicazioni.owl#affiliazioni
  • Politecnico di Milano (Italy), University of Southampton (U.K.), IFAC-CNR (Italy), ESA/ESOC (Germany) (literal)
Titolo
  • End-of-life Earth re-entry for highly elliptical orbits: the INTEGRAL mission (literal)
Abstract
  • This article presents the design of the end-of-life disposal of spacecraft in Highly Elliptical Orbits through Earth re-entry. The effect of luni-solar perturbations can be enhanced through impulsive maneuvers to move the spacecraft on a trajectory that will naturally evolve in the long-term towards Earth re-entry. The dynamics is propagated through semi-analytical averaging techniques, implemented in the PlanODyn suite. Moreover, the analytical approach to describe third-body perturbation by Kozai is used to validate the solution for optimal disposal maneuvers obtained through global optimization. For INTEGRAL mission, re-entry is possible with the available ?v onboard, provided that the orbital dynamics is wisely exploited to enhance the effects of the maneuver. (literal)
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