Managment at deploying a tethered system in elliptical orbit

Management at deploying a tethered system, located in an elliptical Earth orbit is viewed. Orbital system consists of two spacecraft connected by a tether. The new nominal control program depending on the elliptical orbit parameters and providing deployment of the tether system in a given vertical position is offered. Lagrange's method of mathematical model of motion of the system, taking into account the peculiarities of this problem is obtained. Testing calculations are carried out using a mathematical model of motion of the system with distributed parameters recorded in the fixed geocentric coordinate system. System of the stabilization, implementing feedback on the length and speed of the tether is used.