Modeling and comparative analysis of schemes for returning a payload using a space tethered system

The multiple schemes for returning a payload from LEO using a space tethered system are designed and analyzed in this paper. The space tethered system consists of a main spacecraft, a tether, a returning capsule with the payload (or space debris) and an atmospheric probe. The simulation for the motion of the tethered system is based on a mathematical model with distributed parameters, in which the tether is considered as a sequence of point masses with one-sided elastic mechanical coupling. The aerodynamic forces acting on all parts of the tethered system including on the tether are considered in this work. The atmospheric probe is used as an additional braking device for the proposed schemes for returning the payload.