Date of Award

Spring 5-1994

Document Type

Thesis - Open Access

Degree Name

Master of Science in Aerospace Engineering


Graduate Studies

Committee Chair

Habib Eslami

Committee Member

Frank Radosta

Committee Member

Sathya Gangadharan


The purpose of this thesis is to study the nonlinear analysis of antisymmetrically laminated composite beams including shear deformation subjected to harmonic excitation, using a 20-degree of freedom finite element beam. The beam has 10 degrees of freedom at each node: The axial displacements, the transverse deflection due to bending and transverse shear, the twisting angle, the in-plane shear rotation, and their derivatives along the axial direction. In this study, the effect of different parameters such as damping, shear deformation and different edge conditions on the steady-state frequency-responce will be investigated. The analysis was based on the use of finite element methodology for composite laminated beam structures. The harmonic force matrix represents the externally applied force in matrix form, instead of a vector form. Thus the analysis of nonlinear forced vibration can be performed efficiently to get a converged solution. The analysis was also based on the nonlinear stiffness matrix and both in-plane longitudinal, and transverse deflections are included in the formulation. The amplitude-frequency ratios for different boundary conditions, lamination angles, number of plies and thickness to length ratios are presented. The finite element results are compared with available approximate continuum solutions.