Nonlinear Decoupling Control of a Spacecraft

Abstract In this paper a new approach to the nonlinear decoupling control problem using static state feedback is applied to the model of a spacecraft. The general analytical expression for the control law, which leads to a decoupled closed-loop system, is derived. Moreover, it is proven that appropriate selection of the arbitrary parameters of the control law leads to a closed-loop system with linear input-output description and arbitrarily assignable eigenvalues.