Author(s)

Nabawia S. Khalifa

National Research Institute of Astronomy and Geophysics (NRIAG), Helwan, Egypt.

The dynamics of satellites formation is of great interest for the space mission. This work discusses a more efficient model of the relative motion dynamics of satellites formation. The model is based on employing the concepts restricted three-body problem (R3BP) and for more accuracy, it considers the effects of both oblateness and radiation pressure on deputy relative motion w.r.t the chief satellite. A model of deputy relative motion w.r.t the chief satellite is derived in the local-vertical local-horizontal system and simplified assuming the concept of the circular restricted three-body problem (CR3BP). The deputy equations of motion were rewritten in the form of recurrence relations and solved numerically using the Lie series approach. Assuming that the formation is revolving around the Moon in the Earth-Moon system, the effects of both oblateness and radiation pressure on the deputy satellite orbit were assessed through a particular example of satellites formation. A comparison between the perturbed and unperturbed R3BP shows a significant difference in the deputy relative position that has to be considered for the formation dynamics.

Relative Motion, Restricted Three-Body Problem, Lie Series Integration

Khalifa, N. (2022) Dynamics of Satellite Formation Utilizing the Perturbed Restricted Three-Body Problem. Journal of Applied Mathematics and Physics, 10, 219-235. doi: 10.4236/jamp.2022.101016.