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 L4. 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 L4, 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.

The authors acknowledge help and support from the Space Trajectories and Applications Research (STAR) and Advanced Autonomous Multiple Spacecraft (ADAMUS) research groups at Embry-Riddle Aeronautical University, United States, Daytona Beach. Drs. Fors and Gómez acknowledge the support by the Spanish Ministerio de Ciencia e Innovación (MICINN), Spain under grant PID2021-125627OB-C31 and through the “Center of Excellence María de Maeztu 2020–2023” award to the ICCUB (CEX2019-000918-M). Dr. Fors also acknowledges the support by the Spanish Ministerio de Ciencia e Innovación (MICINN), Spain under grant PID2019-105510GB-C31.

Peer reviewed