THE BEHAVIOR OF A SATELLITE TRAJECTORY NEAR THE EQUILIBRIUM POINTS OF SUN-EARTH SYSTEM AND ITS CONTROL
Ali, Noha A.; Shalby, Lina;
Abstract
In this paper, the behavior of a satellite trajectory near the equilibrium points of the Sun-Earth system is studied. The equations describing the motion of the satellite in the circular restricted three body problem for the Sun-Earth system, are discussed for their ordinary differential equations form, and Lagrange points are determined. Then, the stability is studied at each Lagrange point. The trajectories of a satellite starting its motion near Lagrange points are illustrated, showing the stability and instability behavior. Finally, the unstable trajectory is controlled by using l2 -method at L1 as an example.
Other data
| Title | THE BEHAVIOR OF A SATELLITE TRAJECTORY NEAR THE EQUILIBRIUM POINTS OF SUN-EARTH SYSTEM AND ITS CONTROL | Authors | Ali, Noha A.; Shalby, Lina | Keywords | chaos | circular restricted three body problem | Lagrange points | stability | Issue Date | 1-Jan-2023 | Journal | Theoretical and Applied Mechanics | ISSN | 14505584 | DOI | 10.2298/TAM220816003S | Scopus ID | 2-s2.0-85165455535 |
Recommend this item
Similar Items from Core Recommender Database
Items in Ain Shams Scholar are protected by copyright, with all rights reserved, unless otherwise indicated.