Аннотация:We study motions of a light spacecraft equipped with a solar sail near a heavy gravitationally stabilized heliocentric space station. We claim that in this situation the spacecraft relative motion is caused by the solar radiation pressure mainly. Moreover, we find out that if the spacecraft motion is somehow restricted by tether(s) then this pressure can produce acceleration directed at an obtuse angle to the sunlight rays. We suggest some algorithms of selection of the solar sail orientation to provide the spacecraft motion along trajectories realized by the tether(s) in the orbital frame of references. Particularly, we construct the diagram of the sail optimal orientation for motions along a given trajectory in both directions. Also, we establish that if the spacecraft is joined with the station by one tether then a number of the spacecraft motions can be considered as small perturbations of the spherical pendulum motions, in particular, of conic motions.