Aircraft Nonminimum Phase Control in Dynamic Sliding Manifolds

Abstract

The approximate causal nonminimum phase output tracking problem is considered for an F-16 nonlinear sixdegree-of-freedom modelandaddressed via sliding modecontrol.Asymptoticoutputtracking-errordynamicswith desired eigenvalue placement are provided in case of tracking causal reference output proe le with a e nite number of nonzero time derivatives (piecewise polynomial spline model ) in the presence of unmatched disturbances of the same kind. A complete constructive algorithm for tracking controller design is built for a class of uncertain nonlinear multi-input/multi-output systems with known linear unstable internal dynamics. An analysis is made of the issue that the given nonlinear aircraft model yields to the approach developed.