NON-SMOOTH CONTROL OF BIFURCATION PHENOMENA IN AIRCRAFT FLIGHT

摘要

Analysis and control of bifurcation phenomena occurring in aircraft flight have been reported in a number of recent studies. It has been shown that smooth nonlinear feedback is capable of enlarging the region of stability near critical parameters for aircraft models. An integrated approach employing generalized normal forms reduction for both analysis and smooth control of aircraft instabilities has been presented in our recent paper. In this paper we examine how a more efficient compound resonance control consisting of non-smooth and smooth components stabilizes transition behavior coupled with bifurcation of codimension two found in a nonlinear plant modeling aircraft flight. It is shown mat such control essentially reduces the magnitude of smooth feedback gain and simultaneously provides the desired decay of distortion.