Flight time optimization of cylindrical constrained solar sail trajectories
In this paper, we use the surface constraint approach in solving the equation of motion of a solar sailing spacecraft and in determining the optimal flight time trajectories for the case when the sail is constrained on a cylindrical surface. In this approach, a generalized Laplace-Runge-Lenz vector and a constraint based on the geometry of the surface are used to obtain the radial and azimuthal trajectory equations of the sail. We consider the case when the polar and azimuthal components of the unit normal to the sail are periodic with respect to the polar angle of the sail. Finally, we determine the minimum time it takes for the sail to reach an asteroid with a highly-inclined orbit.