Course information

Responsible Instructor
Name E-mail
Dr. C. Kassapoglou    C.Kassapoglou@tudelft.nl
Instructor
Name E-mail
Dr. M.M. Abdalla    M.M.Abdalla@tudelft.nl
Contact Hours / Week x/x/x/x
0/0/4/0
Education Period
3
Start Education
3
Exam Period
none
Course Language
English
Required for
AE4 510 II
Expected prior knowledge
Basic mechanics, classical laminated plate theory, first ply failure criteria, basic differential equations and infinite series
Course Contents
This is the former AE4 510 Part I modified in certain areas to include some comparisons with metals. It introduces the basic components of an airframe structure and discusses their use and limitations. The realities of composite design such as the effect of material scatter, environmental knockdowns, and damage knockdowns are discussed and guidelines accounting for these effects and leading to robust designs are presented. The resulting design constraints and predictive tools are applied to real-life design problems in composite structures. A brief revision of lamination theory and failure criteria leads into the development of analytical solutions for typical failure modes for monolithic skins (layup strength, buckling under combined loads and for a variety of boundary conditions) and stiffeners (strength, column buckling under a variety of loads and boundary conditions, local buckling or crippling for one-edge and no-edge-free conditions). These are then combined into stiffened composite structures where additional failure modes such as skin-stiffener separation are considered. Analogous treatment of sandwich skins examines buckling, wrinkling, crimping, intra-cellular buckling failure modes. Once the basic analysis and design techniques have been presented, typical designs (e.g. flange layup, stiffness, taper requirements) are presented and a series of design guidelines (stiffness mismatch minimization, symmetric and balanced layups, 10% rule, etc.) addressing layup and geometry are discussed. On the metal side, the corresponding design practices and analysis methods are presented for the more important failure modes (buckling, crippling) and comparisons to composite designs are made. A design problem is given in the end as an application of the material in this Part of the cours
Study Goals
Provide a link between standard introductory courses in metals and composites and actual applications with focus on composite structures. It is a summary of the main methods used to design and analyze composite and metal structures in practice. Show how some of the approximate methods used in design can be derived and what the limitations of such methods are.
Education Method
Lectures
Computer Use
access to classical laminated plate theory and first ply failure software
Literature and Study Materials
Lecture notes and textbook
Books
Design and Analysis of Composite Structures by C. Kassapoglou, 2nd Edition, Wiley book publishing
Assessment
4 Problem sets (homework problems) covering material presented in the lectures. One final project
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