Date of Award

Fall 2009

Document Type

Thesis - Open Access

Degree Name

Master of Aerospace Engineering


Graduate Studies

Committee Chair

Dr. Habib Eslami

Committee Member

Dr. Frank J. Radosta

Committee Member

Dr. Sathya Gangadharan


The main purpose of the following analysis is to develop an analytical method for determining the natural frequency of a symmetric composite box-beam subjected to temperature gradient. A set of coupled partial differential equations of motion is obtained by means of small defection theory and D'Alembert's method. The Smith and Chopra stiffness matrix is used in the governing equations of motion and an appropriate MATLAB® code has been written to solve for the stiffness matrix elements of the box-beam. The resulting governing equations of motion are solved to obtain the natural frequencies of the box-beam in flap and lag directions using Galerkin's method. Finally, an example solution for symmetric composite box-beam of [+45°; ±45°] layup using cantilever boundary conditions is presented. For validation of the current analysis, comparisons are made with previously published results.