Computer Science
Scientific paper
Apr 1984
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1984cemec..32..371h&link_type=abstract
Celestial Mechanics (ISSN 0008-8714), vol. 32, April 1984, p. 371-388.
Computer Science
Aerodynamic Drag, Gravitational Effects, Orbit Calculation, Satellite Orbits, Two Body Problem, Deceleration, Equations Of Motion, Kinematics, Vector Analysis
Scientific paper
Nonlifting orbital motion in a central inverse-square gravitational field is presently given by an approximate two-body semianalytical solution, which includes drag whose deceleration is a nonlinear function of velocity (relative to a rotating atmosphere) due to dynamic pressure and a velocity-dependent drag coefficient. Orbital motion in light of this solution occurs in an earth-fixed, invariable plane that is defined by the radius and relative velocity vectors. The simplified equations of motion are autonomous and independent of the central angle measured in the invariable plane, so that the reduction of the differential equations from sixth to second order is possible. General atmospheric density and drag coefficient models may be used to evaluate the velocity quadratures to which radial and circumferential component solutions are reduced.
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