Aeroservoelastic Optimization of a High Aspect Transport Wing with Morphing Trailing Edge

The flutter characteristics of a high aspect ratio wing with morphing trailing edges are analyzed based on the assumption mode method and Double-Lattice Method. The unsteady aerodynamic forces are approximated as rational functions by Minimum-State method, and the effect of compliant morphing trailing edge on the wing dynamic response is investigated. A Linear Quadratic Gaussian regulator is designed to explore the potential of suppressing wing flutter by deflecting the morphing trailing edges actively. Active suppression of aeroelastic response by controlling the trailing edge deflection validated through numerical simulations in the time domain. The simulation results show that the morphing trailing edges can increase the flutter boundary and change the flutter frequency.