This study examines the impact of electric solar wind sail (E-sail) parameters on the attitude stability of E-sail's central spacecraft by using a comprehensive rigid-flexible coupling dynamic model. In this model, the nodal position finite element method is used to model the elastic deformation of the tethers through interconnected two-node tensile elements. The attitude dynamics of the central spacecraft is described using a natural coordinate formulation. The rigid-flexible coupling between the central spacecraft and its flexible tethers is established using Lagrange multipliers. Our research reveals the significant influences of parameters such as tether numbers, tether's electric potential, and solar wind velocity on attitude stability. Specifically, solar wind fluctuations and the distribution of electric potential on the main tethers considerably affect the attitude stability of the spacecraft. For consistent management, the angular velocities of the spacecraft must remain at target values. Moreover, the attitude stability of a spacecraft has a pronounced dependence on the geometrical configuration of the E-sail, with axisymmetric E-sails proving to be more stable.

A floating partial space elevator (PSE) is a PSE with a floating main satellite. This work aims to keep the orbital radius of the main satellite of a floating PSE in cargo transposition without the use of thrusts. A six-degree-of-freedom two-piece dumbbell model was built to analyze the dynamics of a floating PSE. By adjusting the climber’s moving speed and rolling of the end body, the main satellite’s orbital radius can be kept. A novel control strategy using a proportional shrinking horizon model predictive control law containing a self-stability modified law is proposed to stabilize both the orbital and libration states to regulate the speed of only the climber. Simulation results validated the proposed control strategy. The system provides a successful approach to the desired equilibrium by the end of the transposition.