Active flutter suppression for a wing model

Abstract

The paper presents an experimental verification of a method to design active control flutter suppression systems that allows eigenstructure assignment directly within a/?-A flutter approximation. By using a wing model, it is shown how different and simple direct feedback control laws can be effective in producing a substantial improvement of the flutter speed and of the overall damping below the critical speed. Difficulties encountered in correlating designs to test by using a Maximum Likelihood identification method are also addressed.