Abstract: This paper considers the design and dynamics of spacecraft distant from an asteroid, whose gravitational attraction can be neglected at leading order. The motion of the spacecraft then is a function of solar gravity and solar radiation pressure. The differential acceleration between the spacecraft and the small asteroid creates a unique relative dynamics between the two bodies, and provides the spacecraft certain orbits that will remain in the vicinity of the asteroid and which could be used advantageously for observations. The current paper completely solves the simpler case when the asteroid is in a circular heliocentric orbit. The elliptic case is also considered and formulated, with some initial results identified.