HEOSAT: a mean elements orbit propagator program for highly elliptical orbits

  1. Lara, M. 2
  2. San-Juan, J.F. 2
  3. Hautesserres, D. 1
  1. 1 CCT-Centre National d’Études Spatiales, 18 Av. Edouard Belin, Toulouse Cedex, France
  2. 2 Universidad de La Rioja
    info

    Universidad de La Rioja

    Logroño, España

    ROR https://ror.org/0553yr311

Revista:
CEAS Space Journal

ISSN: 1868-2502

Año de publicación: 2018

Volumen: 10

Número: 1

Páginas: 3-23

Tipo: Artículo

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DOI: 10.1007/S12567-017-0152-X SCOPUS: 2-s2.0-85042440385 WoS: WOS:000425789800002 GOOGLE SCHOLAR

Otras publicaciones en: CEAS Space Journal

Repositorio institucional: lock_openAcceso abierto Postprint

Resumen

The algorithms used in the construction of a semi-analytical propagator for the long-term propagation of highly elliptical orbits (HEO) are described. The software propagates mean elements and include the main gravitational and non-gravitational effects that may affect common HEO orbits, as, for instance, geostationary transfer orbits or Molniya orbits. Comparisons with numerical integration show that it provides good results even in extreme orbital configurations, as the case of SymbolX. © 2017, CEAS.