Low-thrust orbit raising with coupled plane change and J(2) precession

The dynamics of low-thrust orbital transfer vehicle under the action of earth-oblateness perturbations has been considered. A set of coupled, orbit-averaged equations have been derived,which may be solved sequentially. Analytic solutions for semimajor axis, true anomaly, inclination, and ascending node angle have been obtained. These solutions extend previous, well-known solutions for low-thrust spiral motion and may be used for mission analysis and design purposes.