  This paper presents a mission concept that enables Earth-Mars communications
resistant to periods of solar conjunction by using CubeSat satellites equipped
with a solar sail. The dynamics of the satellite is modeled separately in the
respective Earth-Sun and Mars-Sun Restricted Three Body Problem (RTBP),
modified to include the solar radiation pressure effect exerted on the sail.
Due to the non-linearities presented on this model, we numerically determine
the location of the non-eclipsed equilibrium points parameterized by the sail
orientation through a continuation method. These are the points where two
CubeSat nanosatellites equipped with a solar sail could be placed. The
instability of these equilibrium points makes it necessary to implement a
control strategy to keep the satellite's trajectory close to equilibrium by
constantly changing the orientation of the sail. To prove the robustness of the
strategy, some numerical simulations have been performed for a given period of
mission.
