Orbital Evolution of Space Debris

Abstract

In order to obtain a complete picture of the time dependent dynamic of 360 fragment in space, the program IODS(ISSA Orbit Determination System) has been set up. Using The program IODS, all fragments orbit of one break-up event can be generated. Perturbation due to the Earth's asymmetrical potential, the Sun, moon, air drag, and solar radiation force are considered. We summarize our results as follows; Due to J2 term, precessional motion of all fragment orbits are 0.5 day < d/dt < 1.4/day) The other perturbations have very small effect.