RESONANCE CONTROL OF AIRCRAFT INSTABILITIES BY SMOOTH AND CONTINUOUS FEEDBACK

Analysis and control of bifurcation phenomena occurring in high angle-of-attack aircraft flight have been the subject of a number of recent studies. It has been shown that smooth nonlinear feedback is capable of stabilizing nonlinear transient phenomena In a certain range of parameters of aircraft models. In a recent paper we presented an integrated approach employing the normal forms reduction methodology for both analysis and control of aircraft instabilities. In this paper we describe a novel resonance control design approach that assumes feedback as a composition of continuous (nonsmooth) and smooth nonlinear components. We show that such compound resonance control matches superior performance with a reduction of feedback magnitude required for stabilization.