Simulation analysis of orbital parameters of small satellite launching by space tether system

Two ways of launching small satellite to elliptical orbit and circular orbit are presented for the problems of using space tether system launching a small satellite. Through two mobile launching ways, the apogee height and perigee height of the small satellite are calculated both in elliptic orbit and approximate circular orbit. Then, Simulation analyzing the influence of the tether length, slip angle and the disturbance of in-plane angle on the apogee height and perigee height of the small satellite. The dynamics equations of the tether system are established in the orbital coordinate system, then, the initial velocity of small satellite is calculated. In order to establish the motion states of small satellite after cutting off the tether, the orbit equations of small satellite are established in the geocentric orbit coordinate system. After the simulation analysis, the optimal end points are obtained, which provide the theoretical basis for selection of end point of space tether system up deployed.