Print Email Facebook Twitter Semi-analytical solutions for buckling and post-buckling of composite plates Title Semi-analytical solutions for buckling and post-buckling of composite plates: Application to stiffened Panels Author Cabot Talens, E. Contributor Kassapoglou, K. (mentor) Faculty Aerospace Engineering Department Aerospace Structures and Computational Mechanics Date 2016-08-25 Abstract This MSc thesis addresses the study of buckling and post-buckling of composite plates with elastic restraints at the edges and under any combination of in-plane loading, aiming to solve the plate response in stiffened panel structures. The implemented solutions are based on thin plate theory for mid-plane symmetric plates. The governing equations are solved using a semi-analytical formulation (not closed form) to combine advantages from analytical and numerical analysis. This approach allows to solve most of the typical laminates used in aerospace applications while allowing an improved performance when compared to FE models. The developed formulation relies on eigenbeam functions to approximate the plate behaviour for any combination of arbitrary elastic restrains, with a minimum number of degrees of freedom. This approach has proved to be able to reproduce the buckling mode and load for buckling and the out-of-plane displacement for post-buckling. The results obtained have been verified against FE commercial software package Abaqus and good to excellent agreement has been achieved using a fraction of the computational power. The relation between the ideal torsional springs and stiffeners’ restrain is approximated in order to apply the developed formulations to more practical problems involving stiffened panels. Preliminary verifications show the validity of the proposed approaches and encourages the further development of the solution to achieve a more powerful stiffened panel formulation. Moreover, the developed approaches can be extended to solve other relevant stability phenomena such as global buckling or stiffener crippling. This work is part of a Fokker Aerostructures project to develop an analytical framework for analysis and design of composite stiffened panels with post-buckling capabilities. This framework will facilitate the preliminary design of composite stiffened structures and allow further optimization without requiring the prohibitive computational cost and complexity of finite element models. Subject bucklingpost-bucklingplatessemi-analyticalcomposite laminatescombined loadingrotationally-restrainedstiffened panels To reference this document use: http://resolver.tudelft.nl/uuid:deb7f375-e5ae-4711-8b1f-41153444d5b5 Part of collection Student theses Document type master thesis Rights (c) 2016 Cabot Talens, E. Files PDF MSc Thesis FR.pdf 3.92 MB Close viewer /islandora/object/uuid:deb7f375-e5ae-4711-8b1f-41153444d5b5/datastream/OBJ/view