Dynamics and active feedback control of wing-type structures modeled as thin-walled beams: implications of beam cross-section nonuniformity

A study of the dynamical behavior of aircraft wings modeled as doubly-tapered thin-walled beams, and incorporating transverse shear effects is presented. In addition, this article also addresses the problem of vibration feedback control of such structures, and to this end, the concept of piezoelectrically induced boundary moment control is applied. The supplied numerical results illustrate the effects played by the taper ratio and transverse shear on open/closed loop free vibration and dynamic response to time-dependent external excitations. Although considered for aircraft wings, the analysis and results can also be applied to large categories of structures such as helicopter blades, robotic manipulator arms, space booms, tall cantilever chimneys, etc.