DescriptionThe stability of a satellite near the Lagrange points is studied in a Circular Restricted Three-Body Problem (CR3BP). The Runge Kutta method is used to trace out the orbital path of the satellite over a period of time. Various initial positions near the Lagrange points and velocities are used to produce various paths the satellite can take. The primary paths focused are on horseshoe paths.
Horseshoe orbits are shown to be sometimes stable and sometimes chaotic.