Functions that determine stability of rational rotations of a near symmetric satellite

Sergey Sadov

Mathematics and Computers in Simulation (MATCOM), 1998, vol. 45, issue 5, 465-484

Abstract: The satellite oscillation equation is a nonlinear second order ordinary differential equation with two parameters, one of which is supposed to be small and the second (the orbit eccentricity e) varies up to a singular value. We discuss the computation of the leading coefficient of the averaged equation (i.e. first approximation of the normal form) in cases of integer and rational mean angular velocity. A regularization near the singular value e=1 is described. An effective qualitative control of the computations is provided by comparing numeric results with control asymptotics obtained by the saddle point method.

Keywords: Averaging; Satellite oscillations; Saddle point method; Normal form; Nonlinear ordinary differential equations; Recurrent relations; Rotation number; Large eccentricity; Regularization of integrals (search for similar items in EconPapers)
Date: 1998
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Persistent link: https://EconPapers.repec.org/RePEc:eee:matcom:v:45:y:1998:i:5:p:465-484

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