The investigations of the influence of aerodynamics on the motion of an artificial
two solid satellite-link a reconditioned by the expansion of their field of application to
orbital large extension tether systems. Aerodynamic effects are quite significant for such
large space systems. The paper considers the classification of cylindrical phase space
limit cycles and also researches the form of the limit cycle for the equation of the relative
motion of two bodies orbital link with the influence of the gravitational effect,
aerodynamic pressure, aero-gradient and dissipative factors, depending on the
eccentricity growth and aerodynamic parameter. We use the associated motion equations
taking into account gravity gradient and aerodynamic factors. An assessment of the
influence of eccentricity and aerodynamic parameter changes on the behavior of limit
cycles is also given in the paper. The research applies well-known methods of nonlinear
mechanics: Lagrange equations of the first kind, the phase plane method, a numerical
implementation of the point mapping method and stability theory methods.
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