LITMIR.BIZ

This book presents the principles of composite laminate sizing widely used for composite structures. The focus is on aeronautics in particular, including the concepts of limit loads and ultimate loads. After a brief overview of the main composite materials used in aeronautics, the basic theory of laminated plates and the associated rupture criteria are given. The author presents two fundamental cases of the sizing of aeronautical composite structures: the calculation of the holed structures and their subsequent multi-bolt joints, and the calculation of the buckling. The concept of damage tolerance is also explored, with a focus on its application for tolerance to impact damage. These notions are fundamental for understanding the specificities of the sizing of aeronautical composite structures. The book also contains corrected exercises for the reader to test their understanding of the different topics covered.

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The objective of this work on the mechanics of aeronautical solids, materials and structures is to give an overview of the principles necessary for sizing of structures in the aeronautical field. It begins by introducing the classical notions of mechanics: stress, strain, behavior law, and sizing criteria, with an emphasis on the criteria specific to aeronautics, such as limit loads and ultimate loads. Methods of resolution are then presented, and in particular the finite element method. Plasticity is also covered in order to highlight its influence on the sizing of structures, and in particular its benefits for design criteria. Finally, the physics of the two main materials of aeronautical structures, namely aluminum and composite materials, is approached in order to clarify the sizing criteria stated in the previous chapters. Exercises, with detailed corrections, then make it possible for the reader to test their understanding of the different subjects.

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