On stability of a satellite motion in elliptical orbit in case of cylindrical precession

Аuthors

Churkina T. E.

e-mail: tatiana802@mail.ru

Abstract

Stability is analyzed for an angular satellite motion in elliptical orbit in case of cylindrical precession. The satellite comes in this case to its initial position revolving on its axis of symmetry within the time of one revolution in the orbit in absolute space. A first approximation of stability regions is obtained in the space of problem parameters including inertial parameter and orbit eccentricity. A detailed nonlinear motion stability analysis is carried out for these regions considering cases with and without 4th order resonances. The stability is inspected for a majority of initial conditions in terms ofLebesgue measure. Regions of parameters values are obtained to satisfy formal stability conditions.

Keywords:

satellite; Hamiltonian function; stability of motion; resonance