Orbital Perturbations and Controlby Solar Radiation Forces

Abstract

Solar radiation pressure induced orbital perturbations are analyzed for a satellite in an elliptic orbit of arbitrary inclination with respect to the ecliptic. The problem is formulated in terms of the two-variable expansion procedure as well as a straightforward perturbation/rectification scheme leading to results valid over a long duration. The vast amount of information generated by a systematic variation of design parameters is condensed in the form of polar plots, from which the long-term in-plane perturbations can easily be visualized. The results show that, in the first order, the semimajor axis remains unchanged in the long run, whereas the eccentricity changes in a periodic fashion. The longitude of the ascending node shows a secular variation which is essentially insensitive to changes in the initial eccentricity. On the other hand, the orbital inclination markedly depends on the initial eccentricity and solar aspect angle. Subsequently, results of controlled on/off switching of the solar radiation force, using several different strategies, are given which represent effective procedures for orbital transfer. A suitable choice of switching strategy can lead to an increase in the semimajor axis by a factor of 10 in less than five years for a spacecraft with an area/mass ratio of 5 m2/kg. Advantages rendered by this capability in terms of scientific exploration, escape, and launch into heliocentric orbits are apparent.