Mathematics
Scientific paper
Feb 1994
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1994em%26p...64..133h&link_type=abstract
Earth, Moon, and Planets (ISSN 0167-9295), vol. 64, no. 2, p. 133-137
Mathematics
Aerodynamic Drag, Earth Atmosphere, Earth Orbits, Eccentric Orbits, Orbital Mechanics, Perigees, Satellite Orbits, Satellite Perturbation, Variations, Altitude, Distance, Earth Surface, Equations Of Motion, Geomagnetism, Graphs (Charts), Mass, Mathematical Models, Solar Activity Effects
Scientific paper
The variations of perturbations in perigee distance for different values of the orbital eccentricity for artificial Earth's satellites due to air drag have been studied. The analytical solution of deriving these perturbations, using the TD model (Total Density) have been applied, (Helali; 1987). The theory is valid for altitudes ranging from 200 to 500 km above the Earth's surface and for solar 10.7 cm flux. Numerical examples are given to illustrate the variations of the perturbations in perigee distance with changing eccentricity (e less than 0.2). A stronge perturbations in the perigee distance have been shown when the eccentricity in the range 0.001 less than e less than 0.05, especially for perigee distance 200 km.
Basurah Hassan M.
Helali Y. E.
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