Computer Science
Scientific paper
Apr 1981
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1981cemec..23..307h&link_type=abstract
Celestial Mechanics, vol. 23, Apr. 1981, p. 307-363.
Computer Science
5
Artificial Satellites, Atmospheric Effects, Earth Orbits, Gravitational Effects, Satellite Drag, Canonical Forms, Differential Equations, Equations Of Motion, Numerical Integration
Scientific paper
An improved analytical solution is obtained for the motion of an artificial earth satellite under the combined influences of gravity and atmospheric drag. The gravitational model includes zonal harmonics through J4, and the atmospheric model assumes a nonrotating spherical power density function. The differential equations are developed through second order under the assumption that the second zonal harmonic and the drag coefficient are both first-order terms, while the remaining zonal harmonics are of second order. Canonical transformations and the method of averaging are used to obtain transformations of variables which significantly simplify the transformed differential equations. A solution for these transformed equations is found; and this solution, in conjunction with the transformations cited above, gives equations for computing the six osculating orbital elements which describe the orbital motion of the satellite. The solution is valid for all eccentricities greater than 0 and less than 0.1 and all inclinations not near 0 deg or the critical inclination. Approximately ninety percent of the satellites currently in orbit satisfy all these restrictions.
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