Abstract
Open- and closed-loop tests for a strain-actuated active aeroelastic wing are summarized. Linear quadratic Gaussian (LQG) control laws as well as robust control laws are designed using sensitivity weighted LQG, classical rationalization, and multiple models. Significant vibration suppression and load alleviation are demonstrated, reducing the power spectral density of the first mode's response by an order of magnitude. The flutter dynamic pressure is increased by 12%. The three major performance limitations are the saturation limit of the piezoelectrics, the choice of performance metric or output sensor, and the changes in the dynamic response of the test article. T
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