Estimating the lifetime and Reentry of the Aluminum Space Debris of Sizes (1-10 cm) in LEO under Atmosphere Drag Effects

H. K. Al-Zaidi, A.M. Taleb, M. J. Al-Bermani



This study concerns in addressing the lifetime and reentry of the space debris in LEO which extends from 200 to 1200 km. In this study the new Computer programs are designed to simulate orbit dynamics of space debris lifetime and reentry under atmospheric drag force by using Runge-Kutta Method to solve the differential equations of drag force and this model was adapted with the Drag Thermosphere Model (DTM78, 94), the Aluminum 2024 space debris in certain size (1-10 cm) were used in this study, which is frequently employed in the structure of spacecraft and aerospace designs. The selected atmospheric model for this investigation is the drag thermospheric models DTM78 and DTM94, because of this dependence on solar and geomagnetic activities. It has been found that the lifetime of the space debris increases with increasing perigee altitudes. It has been found that the elliptical shape of the debris orbit would change gradually into a circular shape, then its kinetic energy would be transformed into heat and hence debris destroy in the dense atmosphere.

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