Temperature effects on failure mode of double lap glass-aluminum and glass-GFRP joints with epoxy and acrylic adhesive (original) (raw)

Experimental study and probabilistic analysis of th e tensile fracture behavior of glass-perlon-acrylic reinforced composi tes for orthopedic use

2014

The effects of the nature of the stacking sequences and the significant influences of the samples cutt ing direction compared with the moulding flux on the tensile mechanical behavior of a set of laminated composite mat erials have been evidenced through analyses of their mecha nical properties. These laminated composite materia ls for orthopedic uses containing acrylic resin reinforced with layers of glass and perlon fibres are arrange d in three differents architectures. A significant scatter is observed on the measurement results of the Young modulus and of the fracture strengths. These latters show highe r values in the perpendicular direction to the moul ding flux. The brittleness measurement, the characterization o f the fracture behavior of these laminates and the probabilistic fracture aspect are quantitatively de scribed through the use of the probabilistic two pa rameters Weibull model. The brittle fracture character of th ese laminates is therefore described by the small ...

Experimental study of repair of aircraft structures by adhesive patches based on epoxy and fiberglass

2019

The composite materials present weakness to shocks and impact, studies are carried out in order to minimize the consequences of these defects, solutions are adopted for temporary or permanent. solutions are adopted for temporary or permanent repairs. These repairs are applied to the defects present on the composite materials of the "Low Energy Impact" type aircraft structure using the Epoxy matrix composite patch method: EPOCASTA50-1, a non-diluted resin reinforced with glass of the same type as that of the aircraft fuselage. The effectiveness of these repairs is verified using the study of conventional tensile behavior. For the characterization of the damaged state and validation of the results, non-destructive NDT control is carried out on specimens developed under the same conditions as repair plates attached to the fuselage plane.

Characterization of the curing reactions of amino resin adhesives and the evolution of rigidity of model wood-adhesive composites by thermal analyses

HAL (Le Centre pour la Communication Scientifique Directe), 1994

Ce traoaii a été effectué au laboratoire de Photochimie .5'l.ppfiquée l (~328 C9{1<S)1 âirigé par Monsieur fe Professeur Xavier '1YE(jLIS'E. Pour {a confiance qu'if m'a témoignée en m'intégrant dans son équipe, pour ses conseils et égafement pour Caide qu'if m'a apportée depuis mon arrivée en France, j'adresse à Monsieur le Professeur Xavier 'D'E(jLIS'E I 'Directeur de {''E9{.SrrFB I mes plus sincères remerciements. Ma profonde reconnaissance va égafement à Monsieur /Daniei M..9LSS09-ft Maître âe Conférences à {''E9{.SrrI13-'llniuetsité de :J{pncy Il qui a âirigé cette thèse et qui m'a fait bénéficier de ses comp étences et de ses idées fructueuses. I'exptime aussi toute magratituâe à Monsieur .5'l.nâré M'E~I9-ft Maître de Conférences à {'Vniversité âe 9{pncy Il pour {es nombreux et pertinents conseils qu'if m'a proâigués.