Explicit Symplectic Integrator for Rotating Satellites

Details Explicit Symplectic Integrator for Rotating Satellites Explicit Symplectic Integrator for Rotating Satellites

Sep 2000

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2000cemda..77..127b&link_type=abstract

Celestial Mechanics and Dynamical Astronomy, v. 77, Issue 2, p. 127-137 (2000).

Astronomy and Astrophysics

Astronomy

2

Numerical Methods, Symplectic Integrators, Satellite Rotation, Numerical Methods, Symplectic Integrators, Satellite Rotation

Scientific paper

An explicit symplectic integrator is constructed for the problem of a rotating planetary satellite on a Keplerian orbit. The spin vector is fixed perpendicularly to the orbital plane. The integrator is constructed according to the Wisdom-Holman approach: the Hamiltonian is separated in two parts so that one of them is multiplied by a small parameter. The parameter depends on the satellite’s shape or the eccentricity of its orbit. The leading part of the Hamiltonian for small eccentricity orbits is similar to the simple pendulum and hence integrable; the perturbation does not depend on angular momentum which implies a trivial ‘kick’ solution. In spite of the necessity to evaluate elliptic function at each step, the explicit symplectic integrator proves to be quite efficient.

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