The end-satellite attitude and tether shimmy combined control method on tether-tugging system

摘要

This paper presents an end-satellite attitude and tether shimmy combined control method under the condition of a free companion flight status between the end-satellite and the space target in the process of tether-tugging. Firstly, a dynamic model for tether-tugging system is established, and the adaptive control sliding mode controller and high-order sliding mode observer are adopted in each channel controller of the model; finally, simulation results prove that the control method designed in this paper can effectively inhibit the swing tether and eliminate the end-satellite attitude coupled motion caused by tether installation point bias, and the control method presents good performance, which has widely application prospects in this space mission.