Integrated Position and Attitude Stabilization of Spacecraft for Eddy Brake based Detumbling

The present study handles the integrated translational and rotational stabilization problem during the space debris detumbling by using eddy brake. By doing so, firstly, a coupled position and attitude dynamics with electromagnetic effect is formulated for a service spacecraft relative to a tumbling debris. An effective model simplification is then conducted such that the nonlinear dynamics can be transformed into a perturbated linear one. In what follows, the parametric method based on eigenstructure assignment for linear systems is utilized to design a feedback controller to guarantee both translational and rotational stabilization. At last, numerical simulation verifies the effectiveness and robustness of the given control strategy.