APPLICATION OF ADAPTIVE TECHNOLOGY TO STATIC AEROELASTIC CONTROL OF WING STRUCTURES

The static aeroelastic behavior of adaptive swept-forward wing structures modeled as thin-walled beams and incorporating piezoelectric effects is investigated. Based on the converse piezoelectric effect, the system of piezoelectric layers, embedded or bonded to the wing, yields control of both divergence instability and, in the subcritical speed range, of aeroelastic lift distribution. The numerical illustrations reveal the ability of adaptive technology to control the static aeroelastic response of swept-forward wings and, as a result, to fully exploit the advantages offered by such a wing configuration.