Compensation of a relative drift of satellites due to the Earth oblateness by the solar radiation pressure

The preprint is devoted to solar sail angle control algorithm development to nullify a relative secular drift due to the Earth oblateness in a Formation Flight motion. It is assumed a satellite’s orbit to be circular and the chief’s orbit not to be controlled to keep the formation. Deputy satellite is equipped with a solar sail. The investigation how to eliminate the relative secular drift by a deputy’s solar sail is carried out. In the work the control to eliminate the relative secular drift is analytically developed. Analytical results are confirmed by numerical simulation of the satellite motion.