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.
","abstract_html":"<p>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.</p>","abstract_has_math":false,"creators":["Chitikela, Lakshmi Narayana Sanjeev"],"institution":null,"degree_name":"Master of Aerospace Engineering","degree_level":"Thesis - Open Access","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":["Habib Eslami","Frank J. Radosta","Sathya Gangadharan"],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2009,"date_issued":"2009-10-01T07:00:00Z","date_published":"2009-10-01T07:00:00Z","updated_at":"2026-07-27T19:25:45Z","subjects":["natural frequency","composites","box-beam","thermal effects","Aerospace Engineering","Structures and Materials"],"languages":[],"rights":[],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"https://commons.erau.edu/db-theses/296","outbound_label":"Repository record","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Habib Eslami","Frank J. Radosta","Sathya Gangadharan"]},{"key":"dc:creator","label":"Author","values":["Chitikela, Lakshmi Narayana Sanjeev"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"thesis:degree_discipline","label":"Discipline","values":["Aerospace Engineering"]},{"key":"thesis:degree_level","label":"Degree Level","values":["Thesis - Open Access"]},{"key":"thesis:degree_name","label":"Degree Name","values":["Master of Aerospace Engineering"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["natural frequency","composites","box-beam","thermal effects","Aerospace Engineering","Structures and Materials"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["https://commons.erau.edu/db-theses/296"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["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.
"]},{"key":"dc:title","label":"Title","values":["An Analytical Investigation of Natural Frequency for a Symmetric Composite Box-Beam with Thermal Effects"]}]}],"canonical_facts":{"dc:contributor":["Habib Eslami","Frank J. Radosta","Sathya Gangadharan"],"dc:creator":["Chitikela, Lakshmi Narayana Sanjeev"],"dc:description.abstract":["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.
"],"dc:identifier":["https://commons.erau.edu/db-theses/296"],"dc:subject":["natural frequency","composites","box-beam","thermal effects","Aerospace Engineering","Structures and Materials"],"dc:title":["An Analytical Investigation of Natural Frequency for a Symmetric Composite Box-Beam with Thermal Effects"],"thesis:degree_discipline":["Aerospace Engineering"],"thesis:degree_level":["Thesis - Open Access"],"thesis:degree_name":["Master of Aerospace Engineering"]},"updated_at":"2026-07-27T19:25:45Z"}