Each part or component in an airframe structure must be designed so that it does not fail under the applied loads and it meets all other design requirements. Usually, the main objective is to keep the weight as low as possible but additional objectives such as minimum cost are also incorporated in the design process. The starting point is the governing equations for a composite plate. These are equilibrium equations, stress—strain equations, and strain—displacement equations. This chapter presents two examples where the governing equations are solved exactly and the results are used in the design of specific applications. For most practical problems, the governing equations described in the chapter cannot be solved exactly and, in some cases, approximate solutions are hard to obtain. As a powerful alternative, energy methods can be used. Minimizing the energy stored in the system or structure can yield useful, approximate and reasonably accurate solutions.


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    Titel :

    Composite Structural Components and Mathematical Formulation


    Beteiligte:


    Erscheinungsdatum :

    2013-05-17


    Format / Umfang :

    59 pages




    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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