Analysis dynamic of deploy tether systems consisting of two nano-satellites

The dynamics of the formation of the space tether system consisting of two nano-satellites in orbit Earth satellite is investigated. Stages of separation of nano-satellites and deployment for a given final length of tether are considered. The mathematical model of the motion of the system, taking into account the angular motion of the end-bodies, stretch tether, the dynamics of the control device to release the tether is designed. For deployment of system simple parametric law, under which provided constraints on the angular motion of nano-satellites to the direction of the tether, is proposed. Comparison of the numerical results obtained by the constructed model and a simpler model of movement of tether system is provided.