Article citationsMore>>

Sanam Suraj, M., Amit, M., Krishan, P. and Deepak, M. (2020) Stability of the Artificial Equilibrium Points in the Low-Thrust Restricted Three-Body Problem When the Smaller Primary Is an Oblate Spheroid. Nonlinear Dynamics and Systems Theory, 20, 439-450.

has been cited by the following article:

• TITLE: Dynamics of Satellite Formation Utilizing the Perturbed Restricted Three-Body Problem

  AUTHORS: Nabawia S. Khalifa

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

  JOURNAL NAME: Journal of Applied Mathematics and Physics, Vol.10 No.1, January 27, 2022

  ABSTRACT: 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.