Boundary moment Control of Free Vibration of Adaptive Aircraft Wings Modeled as Thin-Walled Composite Beams

Yıldız K. , Eken S., Kaya M. O.

8th Ankara International Aerospace Conference, Ankara, Türkiye, 10 - 12 Eylül 2015, ss.1-5

  • Basıldığı Şehir: Ankara
  • Basıldığı Ülke: Türkiye
  • Sayfa Sayıları: ss.1-5


In this study the closed-loop vibrational behavior of aircraft wing is investigated. The wing is modeled as a thin-walled composite beam with a kite type cross section. This beam model incorporates a number of non-classical effects such as material anisotropy, transverse shear deformation and warping restraint. Moreover, the directionality property of thin-walled composite beams produces a wide range of elastic couplings. In this respect, an anti-symmetric lay-up configuration i.e. Circumferentially Uniform Stiffness (CUS) is employed to generate coupled motion of transverse-lateral bending and transverse shear. The active feedback control is performed by using adaptive materials. The piezoelectric layers are symmetrically embedded in the host structure and the piezoactuator is spread over the entire beam span. As a result of this a boundary moment is induced at the beam tip and in this case, the control is achieved via the boundary moment feedback control yielding an adaptive change in the dynamical characteristics of the beam. The cases of proportional and velocity feedback control procedures are applied and the effect of slenderness ratio on the fundamental frequencies are investigated, enhanced and discussed. The results presented in this study will be utilized to obtain a more rational design of advanced aeronautical structures made of composite materials.