Graduation Semester and Year




Document Type


Degree Name

Doctor of Philosophy in Aerospace Engineering


Mechanical and Aerospace Engineering

First Advisor

Wen Chan


A number of methods are available to analyze the laminated composite beams using smear property of laminate stiffness ignoring unsymmetrical behavior of laminates. Some include their effect of laminate but did not include the unsymmetrical effect of the cross-section of the beam. On the other hand, using finite element method to analyze the beam is dependent on the structural configurations including the laminate lay-up sequence. An analytical method was developed from lamination theory in order to study the structural response of composite laminated beams. The present method is capable of predicting the axial and bending stiffnesses, the centroid location, and the stresses in each ply of the whole structure. The results were compared with finite element methods. Laminated beams studied in this research include the beams with a rectangular cross-section bonded with a stiffener. The stiffener placed in both aligned and non-aligned position with respect to the centerline of the beam is considered. Thin-walled beams with circular and airfoil sections are also studied. A parametrization method to define the median of the cross-section is developed. Then the stress analysis is conducted. For two laminates aligned bonded together top and bottom, the present method results agree very well with the finite element results for all the cases less the unsymmetrical case. For the non-aligned case, all the results agree. On the other hand, the results also are close to each other for the laminates bonded side by side less the un-balanced case. Finally, for the circular and airfoil cross-sections the results agree with the finite element results.


Aerospace Engineering | Engineering | Mechanical Engineering


Degree granted by The University of Texas at Arlington