Calculation of perturbations associated with satellite deceleration in the atmosphere

Details Calculation of perturbations associated with satellite deceleration in the atmosphere Calculation of perturbations associated with satellite deceleration in the atmosphere

Jul 1990

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1990kosis..28..531t&link_type=abstract

Kosmicheskie Issledovaniia (ISSN 0023-4206), vol. 28, July-Aug. 1990, p. 531-538. In Russian.

Physics

Atmospheric Entry, Deceleration, Satellite Drag, Satellite Perturbation, Algorithms, Euler Equations Of Motion, Numerical Integration

Scientific paper

An analytical method for calculating perturbations due to satellite deceleration in the atmosphere is proposed which uses an exponential atmosphere model with a variable height scale. The satellite orbit is described by a system of Euler elements. Formulas for calculating the direct effect of satellite deceleration in a stationary atmosphere are obtained, as are formulas allowing for the rotation of the atmosphere. The validity of the analytical formulas is confirmed by the results of numerical integration.

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