抄録
Some studies consider use of an electrodynamic bare tether system for Jovian capture. Almost of previous studies assumed a spinning tether which was given spin period of 20-40 min from tip mass thrust before close to Jupiter. This paper considers that spacecraft using a non-rotating electrodynamic tether system for de-boost in order to achieve transition from Jovian elliptic orbit to a circular orbit. One reason of using a non-rotating tether is that the tether is perpendicular to Jupiter for longer duration than the case of rotating. Because decelerating force is related to spacecraft's attitude and deceleration section of Jovian circles orbit, orbital parameters and attitude motion should be considered to obtain appropriate attitude change resulting from Lorentz force and torque.
