Abstract Atmospheric perturbations of the elements of the artificial satellites orbits are determined using a special model of distribution and variations of the total density of the upper atmosphere between 200–500 km. The model includes diurnal and semi-annual density variations, variations with solar activity and geomagnetic index and latitudinal changes. The height profile is expressed by multiple exponential functions. The equations of motion are solved analytically.
Determination of orbital drag perturbations caused by atmospheric effects
Advances in Space Research ; 6 , 9 ; 151-156
01.01.1986
6 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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