Materiales.Compuestos at 18:54, 30 October 2022

2022-10-30T18:54:35Z

Materiales.Compuestos at 18:54, 30 October 2022

2022-10-30T18:54:01Z

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Scipediacontent at 11:18, 7 May 2022

2022-05-07T11:18:33Z

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Scipediacontent: Scipediacontent moved page Draft Content 421703803 to Fernandez-Canadas et al 2019a

2022-03-31T19:00:20Z

Scipediacontent moved page Draft Content 421703803 to Fernandez-Canadas et al 2019a

Scipediacontent: Created page with "== Abstract == Aircraft structural components made of composite materials are susceptible of being damaged during their service life. The high level of integration and large..."

2022-03-31T19:00:17Z

Created page with "== Abstract == Aircraft structural components made of composite materials are susceptible of being damaged during their service life. The high level of integration and large..."

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== Abstract ==

Aircraft structural components made of composite materials are susceptible of being damaged during their service life. The high level of integration and large size of these structural components may make very difficult the replacement of damaged parts; thus, repair damaged components is a solution that can save economic and temporal costs.
Adhesively-bonded repairs offer certain advantages when compared to mechanical repairs, therefore there is an increasing interest in the study of their mechanical response to static loads, and a detailed structural analysis depend on several parameters.
In this work, a finite-element numerical model was developed in Abaqus/Explicit commercial code. The model was validated experimentally. The numerical model was used to analyse the mechanical response of patch repaired laminates subjected to tensile static loads. The effect of the repair patch shape (rectangular or circular) and repair patch size on the failure load and  elastic stiffness  was evaluated by carrying out a series of virtual tests using the validated numerical model.

== Full document ==
<pdf>Media:Draft_Content_421703803native-articles-237.pdf</pdf>

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 El laminado utilizado en este trabajo está fabricado a partir de un preimpregnado de cinta de fibra de carbono IM7 en resina epoxi MTM-45-1, cuyas propiedades principales se muestran en la Tabla 1. Se usó una secuencia de apilamiento [45/0/-45/90]<sub>s</sub>.
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 Se llevaron a cabo ensayos de tracción estática en una máquina servohidráulica Instron 8516 (Figura 1), a una velocidad de ensayo de 1 mm/min y siguiendo las recomendaciones de la norma ASTM D3039/D3039-14 [<span id='cite-6'></span>[[#6|6]]].
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 En las probetas reparadas con parche circular doble, el espesor de cada uno de los parches correspondía a la mitad del espesor del laminado, por lo que, la secuencia de apilamiento de cada uno de los mismos fue [45/0/-45/90]. El adhesivo empleado para unir laminado y parches fue MTA-240 (Tabla 2).
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 Todas las probetas tenían las mismas dimensiones en longitud y anchura, siendo éstas 250 mm y 50 mm respectivamente. A los extremos de cada probeta se adhirieron talones de fibra de vidrio (de 51 mm x 51 mm), de manera que se impidiera el deslizamiento de la probeta durante la realización del ensayo. En el caso de la reparación, se consideró un parche circular cuyo diámetro fue 30 mm, adherido al laminado mediante una capa de adhesivo tipo film de 0.13 mm de espesor.

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Fernandez-Canadas et al 2019a - Revision history

Materiales.Compuestos at 18:54, 30 October 2022

Materiales.Compuestos at 18:54, 30 October 2022

Scipediacontent at 11:18, 7 May 2022

Scipediacontent: Scipediacontent moved page Draft Content 421703803 to Fernandez-Canadas et al 2019a

Scipediacontent: Created page with "== Abstract == Aircraft structural components made of composite materials are susceptible of being damaged during their service life. The high level of integration and large..."