Time Sensitive Departures in Near Rectilinear Halo Orbits

Satellites in a Near Rectilinear Halo Orbit can utilize unstable manifolds for departure to heliocentric orbits at their end of life. These orbits are highly sensitive to dispersions due to navigation uncertainties and maneuver execution errors. Additionally, uncertainties due to orientation can cause varying effects of solar radiation pressure and out-gassing events can occur after a satellite is no longer operational. This paper characterizes how operators can minimize time of contact with their satellites post-departure while avoiding collisions with other celestial bodies and spacecraft in the orbit used by Earth-Moon’s 9:2 NRHO resonance.