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.

small satellite, solar sail, Formation Flying, relative position control, Earth’s oblateness

Theoretical and applied problems of mechanics