Dynamic stabilization of L2 periodic orbits using attitude-orbit coupling effects Articles uri icon

authors

  • Lara, Martín
  • Peláez Álvarez, Jesús
  • Bombardelli, Claudio
  • Rodríguez Lucas, Fernando
  • SANJURJO RIVO, MANUEL
  • Curreli, Davide
  • LORENZINI, ENRICO
  • Scheeres, Daniel J.

publication date

  • March 2012

start page

  • 73

end page

  • 81

issue

  • 1

volume

  • IV

International Standard Serial Number (ISSN)

  • 2236-577X

abstract

  • URL: http://www.aeroespacial.org.br/jaesa/editions/repository/v04/n01/7-LaraEtAl.pdf ----------------------------------------------------------------------------- RESUMEN: Numerical explorations show how the known periodic solutions of the Hill problem are modified in the case of the attitude-orbit coupling that may occur for large satellite structures. We focus on the case in which the elongation is the dominant satellite's characteristic and find that a rotating structure may remain with its largest dimension in a plane parallel to the plane of the primaries. In this case, the effect produced by the non-negligible physical dimension is dynamically equivalent to the perturbation produced by an oblate central body on a masspoint satellite. Based on this, it is demonstrated that the attitude-orbital coupling of a long enough body may change the dynamical characteristics of a periodic orbit about the collinear Lagrangian points.