Article ID | Journal | Published Year | Pages | File Type |
---|---|---|---|---|
8058596 | Aerospace Science and Technology | 2016 | 10 Pages |
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.
Related Topics
Physical Sciences and Engineering
Engineering
Aerospace Engineering
Authors
Yonmook Park,