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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. An integrated approach employing normal forms reduction methodology for both analysis and control of aircraft instabilities has been presented in our recent paper. In this paper we address a novel resonance control design approach which assumes feedback as a composition of continuous (non-smooth) and smooth nonlinear components. It is shown that such compound resonance control matches superior performance with a reduction of high feedback gain.