Abstract In this paper a robust and optimal attitude control design that uses the minimal kinematic parameters and angular velocities feedback is presented for the three-axis attitude stabilization of spacecraft with inertia uncertainties. After proposing a new class of robust attitude control laws for the three-axis attitude stabilization of spacecraft with inertia uncertainties, it is shown that the proposed robust attitude control laws are optimal with respect to performance indices. A numerical example is given to illustrate the theoretical results presented in this paper.
Robust and optimal attitude control of spacecraft with inertia uncertainties using minimal kinematic parameters
Aerospace Science and Technology ; 54 ; 276-285
2016-04-29
10 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch