Numerical analysis of layered composite panel behavior with interlaminar defects subject to dynamic loads

Aims of research. Polymer unidirectional composite laminate panel behavior with interlaminate defects under action of different dynamic loads is consider. Methods. Normal modes and eigenvalues of rectangular composite panels in the presence multiple delamination different sizes ellipsoidal form are calculated. The dependences of the maximum deflections from the frequency of the stationary pressure field action are constructed. Distribution field of panels plies failure index under action of nonstationary pressure field by using different failure criteria for composites is determined. Results. Modeling methodology composite panels behavior in the presence multiple interlaminar defects under action of different dynamic loads is developed. Analysis of failure panel with the use of different failure criteria for composites is carried out.

PARAMETERIZATION OF NATURAL MODES OF COMPOSITE ROTATING CONICAL SHELLS WITH MULTIPLE DELAMINATION

This paper describes a comparative study on free vibration of bending stiff, torsion stiff and quasi-isotropic graphite-epoxy composite conical shells with single and multiple delamination. The finite element formulation is based on Mindlin's theory and multi-point constraint algorithm neglecting the Coriolis effect for moderate rotational speeds. Computer codes are developed employing QR iteration method to obtain delaminated natural frequencies under combined effect of twist and rotation. Mode shapes are depicted for a typical laminate configuration. The non-dimensional natural frequencies obtained are the first known results which could serve as reference solutions for future investigators.