The longperiod motion of 24hour satellites
Abstract
The longperiod behavior of the Keplerian elements for an earthorbiting 24hour satellite is developed using extended phasespace canonical formalism. The effects of oblateness, equatorial ellipticity, and lunisolar perturbations are included in the developments. Small values of the eccentricity and inclination are assumed. All perturbations are developed through second order in terms of a set of nonsingular variables which are similar to the classical Poincare variables. Lunar motion is described by the secondorder approximation of the HillBrown lunar theory. Solar motion is assumed to be elliptical about the earthmoon barycenter. Resonance due to equatorial ellipticity is handled by a Bohlintype expansion of the Hamiltonian with respect to a reference semimajor axis.
 Publication:

AIAA and AAS, Astrodynamics Conference
 Pub Date:
 August 1976
 Bibcode:
 1976aaas.conf.....R
 Keywords:

 Kepler Laws;
 Orbital Elements;
 Planetary Gravitation;
 Satellite Orbits;
 Synchronous Satellites;
 TwentyFour Hour Orbits;
 EarthMoon System;
 Elliptical Orbits;
 Lunar Gravitational Effects;
 Orbit Perturbation;
 Solar Gravitation;
 Stationary Orbits;
 Three Body Problem;
 Astrodynamics