Composite wing vibration coupling control

The paper discusses the possibility to control coupled bending-twisting vibrations of composite wing by means monoclinic structures in reinforcement plating. Decomposing potential straining energy and kinetic natural vibration modes into interacting non-interacting parts, it became possible introduce two coefficients that integrally consider effect geometry structure upon dynamic response parameters wing. first these describes elastic coupling modes, second coefficient inertial one. numerical studies showing how orientation considerably anisotropic CRP layers plating affects frequencies, loss factors, for several lower tones Besides, each mode, partial values above mentioned were determined relationships orthotropic where instead “free” shearing modulus plant, “pure” is used. Joint analysis obtained results has shown pair bendingtwisting its angle ranges reinforcing caused asymmetry cross-section profile with respect main axes inertia decreases, down complete extinction, due generation material. These are characterized features: 1) difference frequencies investigated minimum 2) belong a stretch restricted corresponding modes. This result practical importance because enables approximate real wings complex existing commercial software packages.