سال انتشار: ۱۳۸۸
محل انتشار: هشتمین همایش انجمن هوافضای ایران
تعداد صفحات: ۳
M. Karami Khorramabadi – Lecturer, Engineering Faculty. Islamic Azad University of Khorramabad, Khorramabad, Iran (corresponding author)
P. Khazaeinejad – Research Associate, Department of Mechanical Engineering, Islamic Azad University of Arak, Arak, Iran
This paper studies the lifetime of ballistic satellites in circular orbits by a numerical solution method. The atmospheric model is based on the Russian’s Gost standard and the solar activities data are used from the Gost standard. The atmospheric density is decreased with height according to the exponential formula. Under the effect of the drag force that is due to the atmospheric density and force of gravity on the satellite, the governing equations system of satellite are derived. Solution of these equations is not possible by the current analytical solutions, thus the Runge-Kotta of four orders is applied to simultaneous solve the equations system. To investigate the accuracy of the present analysis, a compression study is carried out with a real example.