ROBUST CONTROL OF THE MISSILE ATTITUDE BASED ON QUATERNION FEEDBACK

摘要

In this paper, a robust control scheme based on the quaternion feedback for attitude control of the missiles employing thrust vector control is proposed. The control law consists of three parts: the nominal feedback part and an additional term compensating for the aerodynamic moment, and the third part for ensuring robustness to the plant uncertainties. For the proposed control scheme, stability analysis is given, and the performance is shown via computer simulation.