FREE-VIBRATION AND FLUTTER OF DAMAGED COMPOSITE PANELS

A finite element method is investigated for studying the free vibratio n and supersonic flutter analysis of arbitrary damaged composite panel s. The finite element method employs a 48 degrees of freedom (DOF) gen eral plate element and uses the classical lamination theory, microstru ctural continuum damage theory and linearized piston theory. Two diffe rent damage models were investigated. Finite element results are obtai ned to illustrate the effect of damage on the eigenvalues and flutter boundaries. The results obtained indicate that between the two models considered, damage model 1 has a strong influence on both free vibrati on and flutter boundaries. (C) 1997 Elsevier Science Ltd.