Transonic Flutter Suppression Control Law Design and Wind-Tunnel Test Results

Abstract

Fluttersuppressioncontrollawdesignandwind-tunneltestresultsintransonice owforaNACA0012wingmodel, under the benchmark active control technology program at NASA Langley Research Center, will be presented. Two control law design processes using classical and minimax techniques are described. Design considerations for improving the multivariable system robustness are outlined. The classical control law was digitally implemented and tested in the NASA Langley Transonic Dynamics Tunnel. In wind-tunnel tests in air and heavy gas medium, the closed-loop e utter dynamic pressure was increased by over 50% up to the wind-tunnel upper limit. The active e utter suppression system also provided signie cant robustness, relative to gain and phase perturbations, even in the presence of transonic shocks and e ow separation.