Publication: Optimización de componente aeronáutico a través del análisis de composición y configuración de materiales compuestos, por medio de simulaciones con método de elementos finitos
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2017
Defense date
2017-09-27
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Abstract
En el presente proyecto, se busca evaluar la factibilidad de sustituir el material plástico del que está fabricado un conjunto de paneles del techo de cabina de un avión de transporte comercial, por un material compuesto. Se hace una selección de materiales y cálculo de sus propiedades, y aplicando la Teoría Clásica de Laminado, se especifica un laminado adecuado. Posteriormente, con esos datos se realiza la simulación, usando el código comercial de elementos finitos ANSYS, de los paneles usando ambas alternativas materiales, y bajo cargas especificadas en la normativa aeronáutica aplicable, con el propósito de comparar ambas opciones.
Tras analizar los resultados, se llega a la conclusión de que es factible utilizar materiales compuestos para ahorrar peso en paneles interiores de aviones, cumpliendo con los requisitos exigidos a esas piezas.
In the present project, the goal is to evaluate the feasibility of substituting the plastic material of which a set of ceiling panels from the cabin of an airliner are made out of, for a composite material. A materials selection and property calculation is made, and applying Classic Laminate Theory, a suitable laminate is specified. Subsequently, using the data, a simmulation is carried out using commercial software ANSYS to perform Finite Element Method Analysis of the panels using both material alternatives, and under loads specified in applicable aeronautical regulations, with the purpose of comparing both options. After analyzing the results, the conclusión is that it is feasible to use composites to save weight on interior panels of aircraft, meeting all the requirements demanded from these components.
In the present project, the goal is to evaluate the feasibility of substituting the plastic material of which a set of ceiling panels from the cabin of an airliner are made out of, for a composite material. A materials selection and property calculation is made, and applying Classic Laminate Theory, a suitable laminate is specified. Subsequently, using the data, a simmulation is carried out using commercial software ANSYS to perform Finite Element Method Analysis of the panels using both material alternatives, and under loads specified in applicable aeronautical regulations, with the purpose of comparing both options. After analyzing the results, the conclusión is that it is feasible to use composites to save weight on interior panels of aircraft, meeting all the requirements demanded from these components.
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Materiales compuestos, Industria aeronáutica, Teoría clásica de laminado, Elementos finitos, ANSYS