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

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  • Sadov, Sergey

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.

Suggested Citation

  • Sadov, Sergey, 1998. "Functions that determine stability of rational rotations of a near symmetric satellite," Mathematics and Computers in Simulation (MATCOM), Elsevier, vol. 45(5), pages 465-484.
    • Handle: RePEc:eee:matcom:v:45:y:1998:i:5:p:465-484
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