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This paper proposes a framework for a satellite mission with the goal to perform Lunar Occultations within the context of the circular restricted three-body problem (CR3BP) of the Earth-Moon system. This is achieved by exploiting the geometrical relationships between the Earth, Moon, and a spacecraft orbiting around L 4. Additionally, it examines the viability of a linear state-feedback control policy to stabilize short-period orbits under the presence of the gravitational effect of the Sun, Solar radiation pressure, and the Lunar orbital eccentricity, which is not accounted for in the CR3BP dynamics. Given the unprecedented NUV angular resolution achieved by a spacecraft at L 4 , this research proposes a framework for a remote sensing observatory for Solar activity, thereby enabling the monitoring of the entire hemisphere of Solar radiation, and to study different astrophysical issues via Lunar Occultations. • Lunar Occultations are studied by leveraging short-period orbits about L 4. • Short-period orbits (SPO) are selected to increase observation time of the Solar corona. • A linear controller is used to account for unmodeled orbital perturbations. • SPO with lower angular velocity is preferred to observe LO and Kordylewski clouds. • LO from L 4 offer unprecedented NUV angular resolution. [ABSTRACT FROM AUTHOR]