Tethered planetary capture: Controlled maneuvers

A new concept for the application of space tethers in planetary exploration and payload transfer is presented. It is proposed that a payload be deployed on a spinning tether in a hyperbolic orbit in order to provide a sufficient delta-v such that it is captured in an elliptical orbit at the destination planet. Due to conservation of momentum, the main spacecraft gains a 'momentum-enhanced gravity-assist'. This concept is investigated by conducting numerical simulations of a simplified system. The mathematical model is derived using Lagrange's equations including tether mass, but neglects tether vibrations.