Modelling and analysis of the motion of a space tether system in a lunar orbit

The space tethered system in a lunar orbit, consisting of a space station and two small spacecraft, is considered. It is assumed that the space tethered system is fully deployed and makes movements near the local vertical. The center of mass of the station moves in a circular orbit. The space station is considered as a rigid body of finite dimensions. Small spacecraft are considered as material points. The mathematical model of the space system motion is developed using Lagrange equations of the second kind. Parametric analysis of the system oscillations near the local vertical for various mass-geometric characteristics and parameters of the lunar orbit is carried out using the constructed mathematical model. Comparison of the motion of the considered space tethered system with a similar system moving in near-Earth orbit is carried out.