Physics
Scientific paper
Jul 1991
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991baicz..42..219f&link_type=abstract
Astronomical Institutes of Czechoslovakia, Bulletin (ISSN 0004-6248), vol. 42, no. 4, July 1991, p. 219-224. Research supported
Physics
Artificial Satellites, Equations Of Motion, Orbital Mechanics, Satellite Drag, Angular Momentum, Differential Equations, Field Theory (Physics), Perturbation Theory, Two Body Problem
Scientific paper
The general problem of the equations of motion are developed for an artificial satellite with drag when the problem is restricted to the case of a central force field. A force for the drag model is defined which is proportional to the vector velocity and inversely proportional to the square of the distance to the center of attraction. The vector-differential equation of motion is employed to develop the integral of angular momentum for a central force field with drag. A closed-form analytic solution is reached for the two-body problem with a first-order perturbation in the potential function given as 1/r exp 2. Bessel's functions of the first and second kind are used with an asymptotic solution to the linear differential equation to derive the final expression. The effect of drag on the expression for the radius is illustrated numerically for a variety of cases.
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