Abstract
This paper describes an analytical and experimental investigation into the use of active lifting surfaces with distributed strain actuators for dynamic aeroelastic control. A detailed analytical aeroelastic model is developed for analysis and control law design using the Rayleigh-Ritz assumed mode method, kernel function unsteady aerodynamics, and modern state-space techniques. The models are used to design multivariable dynamic compensators for applications such as gust alleviation, command following, and flutter suppression. The effectiveness of the control laws is assessed analytically and verified experimentally through closed-loop wind-tunnel testing. The experiments demonstrate that distributed strain actuation can be effectively employed for aeroelastic control, with gust alleviation of 8-dB broadband and an increase in flutter speed of 11 %.
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