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.
","abstract_html":"<p>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.</p>","abstract_has_math":false,"creators":["Kenareh, Mansour Nosrati"],"institution":null,"degree_name":"Master of Science in Aerospace Engineering","degree_level":"Thesis - Open Access","degree_discipline":"Graduate Studies","degree_department":null,"school":null,"contributors":["Habib Eslami","Frank Radosta","Sathya Gangadharan"],"advisors":[],"committee_chairs":[],"committee_members":[],"year":1994,"date_issued":"1994-05-01T07:00:00Z","date_published":"1994-05-01T07:00:00Z","updated_at":"2026-07-27T19:25:16Z","subjects":["nonlinear analysis","laminated composite beams","harmonic excitation","Aerospace Engineering"],"languages":[],"rights":[],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"https://commons.erau.edu/db-theses/271","outbound_label":"Repository record","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Habib Eslami","Frank Radosta","Sathya Gangadharan"]},{"key":"dc:creator","label":"Author","values":["Kenareh, Mansour Nosrati"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"thesis:degree_discipline","label":"Discipline","values":["Graduate Studies"]},{"key":"thesis:degree_level","label":"Degree Level","values":["Thesis - Open Access"]},{"key":"thesis:degree_name","label":"Degree Name","values":["Master of Science in Aerospace Engineering"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["nonlinear analysis","laminated composite beams","harmonic excitation","Aerospace Engineering"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["https://commons.erau.edu/db-theses/271"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["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.
"]},{"key":"dc:title","label":"Title","values":["Nonlinear Finite Element Analysis of Laminated Composite Beams Subjected to Harmonic Excitations Using a 20 DOF Beam Element"]}]}],"canonical_facts":{"dc:contributor":["Habib Eslami","Frank Radosta","Sathya Gangadharan"],"dc:creator":["Kenareh, Mansour Nosrati"],"dc:description.abstract":["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.
"],"dc:identifier":["https://commons.erau.edu/db-theses/271"],"dc:subject":["nonlinear analysis","laminated composite beams","harmonic excitation","Aerospace Engineering"],"dc:title":["Nonlinear Finite Element Analysis of Laminated Composite Beams Subjected to Harmonic Excitations Using a 20 DOF Beam Element"],"thesis:degree_discipline":["Graduate Studies"],"thesis:degree_level":["Thesis - Open Access"],"thesis:degree_name":["Master of Science in Aerospace Engineering"]},"updated_at":"2026-07-27T19:25:16Z"}