3 credits
Fall 2025 Lecture Distance Learning Upper Division
Properties of wing and fuselage sections. Beam-column moments. Torsion of thin-walled and skin-stringer multiple-cell sections. Nonsymmetrical bending of skin-stringer wing sections. Flexural shear in open and closed thin-walled and skin-stringer sections. Loads and stresses in the rib system. Cutouts and shear lag. Modified beam theory for wing and fuselage design. Deflection by energy method. Introduction to composite structures.
Learning Outcomes1Use analytical/empirical tools for determining the distribution of load (or displacement) in typical aerospace components.
2Understand and implement the procedures for relating applied loads (or displacements) to component "failure".
3Select of materials to resist structural failure.
4Be exposed to other professional development topics are also to be presented as time permits (e.g., technical communications, teamwork issues, economic considerations, engineering ethics, case histories, regulatory and certificiation, topics, etc.).
Prerequisites
GPA by professor
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