Publication: Análisis numérico de impactos de hielo sobre placas de aluminio
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2014-09
Defense date
2014-10-03
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Abstract
El diseño y construcción de los componentes estructurales son temas de gran relevancia dentro de la ingeniería aeroespacial ya que forman parte de elementos críticos dentro en una aeronave, debido a las características propias del entorno donde desarrollan su funcionalidad.
A estos elementos se les debe dotar de unos altos niveles de fiabilidad y de seguridad en su diseño. Consecuentemente, los ensayos experimentales y simulaciones numéricas de los materiales empleados en la construcción de los componentes resultan un aspecto de gran importancia en el sector; ya que permiten evaluar los posibles daños que puedan aparecer en la estructura, así como estudiar configuraciones que permitan reducirlos.
Dada la alta velocidad a la que viajan las aeronaves, un impacto de cualquier agente externo sobre su fuselaje puede dar lugar a fallos que pueden ser catastróficos para la integridad de la estructura.
Este documento pretende hacer un análisis de carácter numérico del impacto de un proyectil de hielo sobre una placa de aluminio, elemento que constituye alrededor del 20% del peso total de una aeronave de última generación; así como la influencia que tienen sobre dicho impacto algunos parámetros asociados tanto al proyectil como a la placa impactada.
En primer lugar, se ha validado el modelo numérico empleado en la simulación haciendo uso de datos experimentales que se reflejan en el artículo experimental realizado por la Agencia Aeroespacial Americana NASA en el año 1971.
Una vez validado el modelo, se pretende realizar una serie de modificaciones en el modelo con el objetivo de estudiar su influencia sobre el impacto. Las variaciones realizadas son las siguientes:
I. Composición del aluminio de la placa impactada.
II. Velocidad de impacto del proyectil.
III. Espesor de la placa impactada.
IV. Masa del proyectil, manteniendo la superficie de contacto idéntica.
V. El volumen y la velocidad del proyectil, manteniendo su energía cinética constante.
Los resultados obtenidos en las diferentes simulaciones han permitido analizar y entender el comportamiento del impacto en determinadas condiciones específicas.
All structural components being part of an aircraft are considered critical elements, due to the natural requirements coming from the scenario where they are commonly deployed. Therefore, their design and construction are highly relevant issues whithin the scopes of aerospace engineering. These types of elements must perform at very demanding security and relaliability levels in terms of design. Consequently, experimental tests and numerical simulations of materials used in the construction of aircraft components become an added value to aeronautical industry, thus avoiding potential failures which could even become unrecoverable. Due to the particularly high speed of most aerial platforms, any impact caused by an external agent in the fuselage may lead to critical situations, even catastrophic; that modern society hardly accepts and tolerates in most cases. The main goal of this document is to analyze hail impact onto an aluminium plate. This material is around of a last generation aircraft weight. Furthermore, Also, it will also be analyze the influence of changing certain parameters associated to the projectile and the target. As a first step, the simulation model must be validated, taking into account experimental test data from a NASA paper published in 1971. Once the model is assumed as correct, some changes will be introduced in the model in order to analyze their influence on the impact results. variations of determined impact parameters are given. Changes will be related to: I. Target´s Aluminium alloy. II. Projecttile´s impacting speed. III. Target plate thickness. IV. Projectile mass, maintaining constant impacting área. V. Projectile volumen & speed, maintaining constant kinetic energy. Obtained results will allow to analyze and understand the hail impact behaviour in certain conditions.
All structural components being part of an aircraft are considered critical elements, due to the natural requirements coming from the scenario where they are commonly deployed. Therefore, their design and construction are highly relevant issues whithin the scopes of aerospace engineering. These types of elements must perform at very demanding security and relaliability levels in terms of design. Consequently, experimental tests and numerical simulations of materials used in the construction of aircraft components become an added value to aeronautical industry, thus avoiding potential failures which could even become unrecoverable. Due to the particularly high speed of most aerial platforms, any impact caused by an external agent in the fuselage may lead to critical situations, even catastrophic; that modern society hardly accepts and tolerates in most cases. The main goal of this document is to analyze hail impact onto an aluminium plate. This material is around of a last generation aircraft weight. Furthermore, Also, it will also be analyze the influence of changing certain parameters associated to the projectile and the target. As a first step, the simulation model must be validated, taking into account experimental test data from a NASA paper published in 1971. Once the model is assumed as correct, some changes will be introduced in the model in order to analyze their influence on the impact results. variations of determined impact parameters are given. Changes will be related to: I. Target´s Aluminium alloy. II. Projecttile´s impacting speed. III. Target plate thickness. IV. Projectile mass, maintaining constant impacting área. V. Projectile volumen & speed, maintaining constant kinetic energy. Obtained results will allow to analyze and understand the hail impact behaviour in certain conditions.
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Keywords
Ensayo de materiales, Método de elementos finitos, Resistencia de materiales, Resistencia frente a impacto