Optimal solar sail transfer to linear trajectories

The aim of this paper is to characterize a mission toward a heliocentric linear trajectory (that is, a rectilinear orbit) and to investigate the performance of a solar-sail-based spacecraft to accomplish the transfer phase using an ideal or an optical force model. A similar problem has been recently discussed under simplified assumptions, but new results are now provided with a thorough analysis that uses a three dimensional transfer orbit or a piecewise constant steering law. The paper investigates a complex mission scenario, where the solar sail returns back to Earth after a scientific probe is released along a target linear trajectory.

► A mission toward a rectilinear orbit may be accomplished using a solar-sail. ► This choice is encouraged by the high Delta V required by a bi-impulsive transfer. ► An orbit with aphelion radius of 5.2 AU requires an acceleration of 3.5 mm/s2. ► The mission can be completed with a flight time of less than 3 years.