A First Order Analytical Solution for Spacecraft Motion about (433)Eros

  1. San-Juan, J.F. 1
  2. Abad, A. 4
  3. Scheeres, D.J. 2
  4. Lara, M. 3
  1. 1 Universidad de La Rioja
    info

    Universidad de La Rioja

    Logroño, España

    ROR https://ror.org/0553yr311

  2. 2 University of Michigan–Ann Arbor
    info

    University of Michigan–Ann Arbor

    Ann Arbor, Estados Unidos

    ROR https://ror.org/00jmfr291

  3. 3 Dept. of Ephemerides, Real Observatorio de la Armada, 11110 San Fernando, Spain
  4. 4 Universidad de Zaragoza
    info

    Universidad de Zaragoza

    Zaragoza, España

    ROR https://ror.org/012a91z28

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Libro:
AIAA/AAS Astrodynamics Specialist Conference and Exhibit

Editorial: American Institute of Aeronautics and Astronautics Inc.

ISBN: 9781624101243

Año de publicación: 2002

Tipo: Capítulo de Libro

SCOPUS: 2-s2.0-84876424213 GOOGLE SCHOLAR

Resumen

The orbital motion of spacecraft about asteroids is highly perturbed, and classical theories for motion close to spheroidal bodies cannot be applied. In particular, this is the case for motion about (433) Eros: its large ellipticity coefficient (having the same order as the oblateness coefficient) and its fast rotation rate dominate the dynamics. In this paper we obtain a first order theory for the motion of a satellite around Eros by means of two Lie transformations. The first one is a simplification of the Hamiltonian expressed in polar-nodal variables by using a new technique, the algorithm of relegation. The second one is the classical Delaunay normalization. After both transformations we replace the actual nonintegrable Hamiltonian by an integrable approximation to it.