Tailless aircraft control law design using dynamic inversion & μ-synthesis

In this paper, a manual flight control system for the combined longitudinal and lateral-directional dynamics of a tailless fighter airplane is presented. The design method used is dynamic inversion combined with structured singular value synthesis to address the issues of stability, performance, and robustness to plant uncertainties. Design objectives are formulated in terms of stability, flying qualities, and robustness achieved by the closed-loop system. The controller structure consists of an inner loop in which equalizes the airplane dynamics across the flight envelope and an outer loop having a robust dynamic controller to provide the tracking performance