Free vibration and flutter of damaged composite panels

• Published in: Composite structures Vol. 38; no. 1; pp. 477 - 481
• Main Author: Pidaparti, R.M.V.
• Format: Journal Article Conference Proceeding
• Language: English
• Published: Oxford Elsevier Ltd 01-05-1997; Elsevier Science
• Subjects: Exact sciences and technology; Fundamental areas of phenomenology (including applications); Physics; Solid mechanics; Structural and continuum mechanics; Vibration, mechanical wave, dynamic stability (aeroelasticity, vibration control...); Vibrations and mechanical waves; Supersonic flow; Finite element method; Composite materials; Aeroelastic flutter; Free vibration; Shells; Numerical method; Aeroelasticity; Damage; Plates
• ISSN: 0263-8223; 1879-1085
• DOI: 10.1016/S0263-8223(97)00082-2

A finite element method is investigated for studying the free vibration and supersonic flutter analysis of arbitrary damaged composite panels. The finite element method employs a 48 degrees of freedom (DOF) general plate element and uses the classical lamination theory, microstructural continuum damage theory and linearized piston theory. Two different damage models were investigated. Finite element results are obtained 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 vibration and flutter boundaries.