Modeling and analysis of oscillations of electrodynamic tether system on orbit of Earth satellite

The dynamics of the electrodynamic tether system while moving in orbit around the Earth is investigated. The electrodynamic tether system consists of two spacecraft and the current conducting tether. For the analysis of oscillations of the tether system in orbit is made to construct a mathematical model of the system using the method of Lagrange. When constructing a mathematical model assumes that the tether is stretched by Hooke's law. The case in which the electrodynamic tether system operates in thrust generation, and a constant electric current is passed through the tether is considered. On the tether, as a conductor, Ampere force acting in the Earth's magnetic field, which is used to change the parameters of the orbit of the considered mechanical system. Numerical and analytical methods are analyzed oscillations of tether system in the gravitational field under the action of a distributed load of Ampere force. Detected and analyzed the effects associated with the interaction of bending and transverse oscillations tether system. It is shown that self-oscillations may occur in the system. Features of oscillations in the system in the plane and in three-dimensional case is considered. Impact on the oscillations in the system the mass ratio of the spacecraft, the current value and other parameters is analyzed. The possibilities of using conductive tethers to change the parameters of the spacecraft orbits are measured. Numerical examples for the most typical cases, oscillations in the system are given.