Analytical Drag Theory of an Artificial Satellite with Small Eccentricity

Abstract

An analytical solution is constructed for the problem of an artificial satellite perturbed by the atmosphere of a non-rotating spherical Earth. All the formulas are presented in explicit form from osculating elements at epoch to osculating elements at date. This solution has been developed as a preliminary study on the feasibility of a more complex and more accurate theory which would take into account the effects of the oblateness of the Earth and possibly other perturbations. The emphasis is thus placed on perturbation techniques open to further extensions either in the order of the method or in the sophistication of the model.