Bioorganic/inorganic hybrid composition of sponge spicules: Matrix of the giant spicules and of the comitalia of the deep sea hexactinellid Monorhaphis

The giant basal spicules of the siliceous sponges Monorhaphis chuni and Monorhaphis intermedia (Hexactinellida) represent the largest biosilica structures on earth (up to 3 m long). Here we describe the construction (lamellar organization) of these spicules and of the comitalia and highlight their organic matrix in order to understand their mechanical properties. The spicules display three distinct regions built of biosilica: (i) the outer lamellar zone (radius: >300 mu m), (ii) the bulky axial cylinder (radius: <75 mu m), and (iii) the central axial canal (diameter: <2 mu m) with its organic axial filament. The spicules are loosely covered with a collagen net which is regularly perforated by 7-10 mu m large holes; the net can be silicified. The silica layers forming the lamellar zone are approximate to 5 mu m thick; the central axial cylinder appears to be composed of almost solid silica which becomes porous after etching with hydrofluoric acid (HF). Dissolution of a complete spicule discloses its complex structure with distinct lamellae in the outer zone (lamellar coating) and a more resistant central part (axial barrel). Rapidly after the release of the organic coating from the lamellar zone the protein layers disintegrate to form irregular clumps/aggregates. In contrast, the proteinaceous axial barrel, hidden in the siliceous axial cylinder, is set up by rope-like filaments. Biochemical analysis revealed that the (dominant) molecule of the lamellar coating is a 27-kDa protein which displays catalytic, proteolytic activity. High resolution electron microscopic analysis showed that this protein is arranged within the lamellae and stabilizes these surfaces by palisade-like pillars. The mechanical behavior of the spicules was analyzed by a 3-point bending assay, coupled with scanning electron microscopy. The load-extension curve of the spicule shows a biphasic breakage/cracking pattern. The outer lamellar zone cracks in several distinct steps showing high resistance in concert with comparably low elasticity, while the axial cylinder breaks with high elasticity and lower stiffness. The complex bioorganic/inorganic hybrid composition and structure of the Monorhaphis spicules might provide the blueprint for the synthesis of bio-inspired material, with unusual mechanical properties (strength, stiffness) without losing the exceptional properties of optical transmission. (C) 2007 Elsevier Inc. All rights reserved.

Performance of clay samples reinforced with vertical granular columns

This paper reports an experimental study in which samples of soft kaolin clay (100 mm in diameter and 200 mm in height) were reinforced with vertical columns of sand and tested under triaxial conditions. Samples were reinforced with either a single column of sand of 32 mm diameter or three columns of sand, each of 20 mm diameter. The replacement method was used to form the columns. The columns were installed in the clay to depths of 120 and 200 mm. Tests were also carried out on samples that were not reinforced with sand columns. The samples were compressed under both drained and undrained conditions. It was found that the undrained shear strength of samples containing full-depth columns was greatly improved compared with that of the unreinforced samples. In the fully drained tests, the sample installed with a single column of 32 mm diameter exhibited better performance than the sample with three columns of 20 mm diameter, although the area replacement ratio in the case of the three 20 mm diameter columns was higher than that of the single 32 mm diameter column. However, the undrained strength of the composite material was not particularly affected by the number of columns.

Compressed Metal Powders that Remain Superhydrophobic After Abrasion

Superhydrophobic “lotus effect” materials are typically not sufficiently robust for most real world applications because their small surface features are both easily damaged and vulnerable to fouling. Here, a method for preparing a new type of superhydrophobic (? > 162°) composite material by compression of superhydrophobic metal particles is reported. This material, which has no natural analogue, has low-surface-energy microstructures extending throughout its whole volume. Removing its outer layer by abrasion or cutting deep into it does not result in loss of superhydrophobicity because it merely exposes a fresh portion of the underlying superhydrophobic material. The high contact angle is therefore retained even after accidental damage, and vigorous abrasion can be used to restore hydrophobicity after fouling.

Numerical analysis of stiffener runout sections

The recent trend of incorporating more composite material in primary aircraft structures has highlighted the vulnerability of stiffened aerostructures to through-thickness stresses, which may lead to delamination and debonding at the skin-stiffener interface, leading to collapse. Stiffener runout regions are particularly susceptible to this problem and cannot be avoided due to the necessity to terminate stiffeners at rib intersections or at cutouts, interrupting the stiffener load path. In this paper, experimental tests relating to two different stiffener runout specimens are presented and the failure modes of both specimens are discussed in detail. A thinner-skinned specimen showed sudden and unstable crack propagation, while a thicker-skinned specimen showed initially unstable but subsequent stable crack growth. Detailed finite element models of the two specimens are developed, and it is shown how such models can explain and predict the behaviour and failure mode of stiffener runouts. The models contain continuum shell elements to model the skin and stiffener, while cohesive elements using a traction-separation law are placed at the skin-stiffener interface to effectively model the debonding which promotes structural failure.

The Behavior of compressively loaded stiffener runout specimens - Part I: Experiments

The development of the next generation of civil and military transport aircraft will inevitably see an increased use of advanced carbon fibre composite material in the primary structure if performance targets are to be met. One concern in this development is the vulnerability of co-cured and co-bonded stiffened structures to through-thickness stresses at the skin-stiffener interfaces, particularly in stiffener runout regions. These regions are a consequence of the requirement to terminate stiffeners at cutouts, rib intersections, or other structural features which interrupt the stiffener load path.

This work presents the results of an experimental programme investigating the failure of thick-sectioned stiffener runout specimens loaded in uniaxial compression. For all tests, failure initiated at the edge of the runout and propagated across the skin-stiffener interface. It was found that the failure load of each specimen was greatly influenced by intentional changes in the geometric features of these specimens. High frictional forces at the edge of the runout were also deduced from a fractographic analysis, indicating a predominantly Mode II initial failure mode.

Failure of thick-skinned stiffener runout sections loaded in uniaxial compression

Recent efforts towards the development of the next generation of large civil and military transport aircraft within the European community have provided new impetus for investigating the potential use of composite material in the primary structure. One concern in this development is the vulnerability of co-cured stiffened structures to through-thickness stresses at the skin-stiffener interfaces particularly in stiffener runout regions. These regions are an inevitable consequence of the requirement to terminate stiffeners at cutouts, rib intersections or other structural features which interrupt the stiffener load path. In this respect, thickerskinned components are more vulnerable than thin-skinned ones. This work presents an experimental and numerical study of the failure of thick-sectioned stiffener runout specimens loaded in uniaxial compression. The experiments revealed that failure was initiated at the edge of the runout and propagated across the skin-stiffener interface. High frictional forces at the edge of the runout were also deduced from a fractographic analysis and it is postulated that these forces may enhance the fracture toughness of the specimens. Finite element analysis using an efficient thick-shell element and the Virtual Crack Closure Technique was able to qualitatively predict the crack growth characteristics for each specimen

Integrating allowable design strains in composites with whole life value

Fibre-Reinforced Plastics (FRPs) have been used in civil aerospace vehicles for decades. The current state-of-the-art in airframe design and manufacture results in approximately half the airframe mass attributable to FRP materials. The continual increase in the use of FRP materials over metallic alloys is attributable to the material's superior specific strength and stiffness, fatigue performance and corrosion resistance. However, the full potential of these materials has yet to be exploited as analysis methods to predict physical failure with equal accuracy and robustness are not yet available. The result is a conservative approach to design, but one that can bring benefit via increased inspection intervals and reduced cost over the vehicle life. The challenge is that the methods used in practice are based on empirical tests and real relationships and drivers are difficult to see in this complex process and so the trade-off decision is challenging and uncertain. The aim of this feasibility study was to scope a viable process which could help develop some rules and relationships based on the fundamental mechanics of composite material and the economics of production and operation, which would enhance understanding of the role and impact of design allowables across the life of a composite structure.

An Experimental Investigation into the Effects of Flanged Holes in Hat-Stiffened Panels Loaded in Uniaxial Compression

The effects of a 100 mm diameter integrally-flanged hole in a hat-stiffenend carbon-fibre composite panel, loaded in uniaxial compression, were investigated and compared with a similar panel containing an unflanged hole. Details of the manufacturing techniques used in the production of the integral flange are presented. The stiffening effects of the flange reduced the bending strains, which may lead to high interlaminar shear strains, around the cutout while increasing the membrane strains. These membrane strains were well below the limit strains for this composite material. The skin in the unflanged hole also underwent a change in buckling mode shape from three longitudinal half-wavelengths to five half-wavelengths. No such change was observed in the flanged panel and this buckled in four longitudinal half-wavelengths. The ultimate strength of both panels was determined by the load carrying capability of the stiffeners.

Impact of Referral Protocols on the Dental Management of Patients Undergoing Treatment for Head and Neck Oncology in Northern Ireland

Objective: To evaluate the handling, by a group of practice-based researchers, of a recently introduced bulk fill resin-based composite restorative material, Filtek Bulk Fill Restorative (3M ESPE).

Methods: The twelve selected evaluators were sent explanatory letters, a pack of the material under investigation to use for 8 weeks, and a questionnaire.

Results: The evaluators rated the ease of use of the bulk fill restorative the same as the previously used posterior composite material. The provision of one shade only for evaluation may have compromised the score for aesthetic quality. No post-operative sensitivity was reported.

Conclusions: The bulk fill material was well received as indicated by the high number of evaluators who would both purchase the material and recommend it to colleagues.

Clinical relevance: A recently introduced bulk fill restorative material achieved a rating for handling which was similar to the evaluators’ previously used resin composite, although there were some concerns regarding the translucency of the material.

Design of New Materials for Passive Vibration Control

The objective of this contribution is to extend the models of cellular/composite material design to nonlinear material behaviour and apply them for design of materials for passive vibration control. As a first step a computational tool allowing determination of optimised one-dimensional isolator behaviour was developed. This model can serve as a representation for idealised macroscopic behaviour. Optimal isolator behaviour to a given set of loads is obtained by generic probabilistic metaalgorithm, simulated annealing. Cost functional involves minimization of maximum response amplitude in a set of predefined time intervals and maximization of total energy absorbed in the first loop. Dependence of the global optimum on several combinations of leading parameters of the simulated annealing procedure, like neighbourhood definition and annealing schedule, is also studied and analyzed. Obtained results facilitate the design of elastomeric cellular materials with improved behaviour in terms of dynamic stiffness for passive vibration control.

Otimização de placas compósitas laminadas utilizando redes neuronais e enxames de partículas

Trabalho Final de mestrado para obtenção do grau de Mestre em engenharia Mecância

Estudo da Delaminação em Compósitos de Epóxido Reforçado com Borracha e Fibras Naturais

Nos últimos anos, a utilização dos materiais compósitos tem vindo a tornar-se cada vez mais comum em várias indústrias, onde se verifica uma ascensão na procura pelos mesmos. Características como o baixo peso aliado à sua alta resistência e rigidez permitem que estes materiais possuam diversas aplicações em variadas áreas, desde a medicina, aeronáutica, indústria automóvel e aeroespacial, até à indústria eletrónica. Hoje em dia, o uso de desperdícios sólidos de borracha e fibras naturais na produção de materiais compósitos é, mais que uma opção, uma necessidade ambiental. De forma a reduzir as enormes quantidades de desperdícios, foi criado um material compósito constituído por uma resina termoendurecível reforçada com esses dois tipos de desperdícios. Parâmetros de fabrico como a percentagem de borracha, o tamanho das partículas de borracha, a percentagem de fibras de cana-de-açúcar e o comprimento dessas fibras foram variados, com o objetivo de estudar a influência destes dois materiais nas propriedades mecânicas do compósito. Apesar da maior parte dos compósitos serem fabricados na forma de uma peça funcional quase pronta a ser utilizada, por vezes é necessário recorrer à maquinação de furos. Apesar das muitas técnicas de furação existentes, os defeitos resultantes deste processo aplicado aos materiais compósitos são ainda muito comuns. Desses defeitos o que mais se destaca é sem dúvida a delaminação. Trinta e seis provetes de epóxido reforçado com borracha e fibra de cana-de-açúcar foram fabricados e furados, de modo a possibilitar o estudo das propriedades mecânicas do material compósito, assim como a análise da zona danificada durante a furação. Diferentes condições de furação, como tipos de broca e velocidades de avanço diferentes, foram impostas aos provetes de forma a variar o mais possível a zona de dano de uns furos para os outros. Parâmetros como a área de dano ou ainda o fator de delaminação provam ser muito úteis na caracterização e quantificação do dano na zona periférica de um furo. Recorrendo a técnicas de processamento de imagem foi possível obter esses parâmetros. O processamento e análise de imagem pode ser feito através de vários métodos. O método utilizado neste trabalho foi o software MATLAB® associado a ferramentas de processamento de imagem. Depois de feita a análise dos furos foram realizados ensaios de esmagamento a todos os provetes. Este passo permitiu assim avaliar de que forma os parâmetros de furação influenciam a resistência mecânica do material, e se a avaliação realizada aos furos é um método viável para a avaliação da extensão de dano nesses furos.

Caracterização de perfis pultrudidos Híbridos

A pultrusão é uma técnica já sobejamente conhecida de produção de perfis de secção constante, tais como barras, cantoneiras, perfis estruturais ou tubos, em materiais compósitos de matriz polimérica. A necessidade de, em determinadas aplicações, utilizar perfis que proporcionem melhor isolamento térmico, melhor isolamento acústico ou possuam um momento de inércia ligeiramente superior, sem que o peso próprio seja significativamente afectado, levou à produção de perfis pultrudidos híbridos, com núcleos baseados em pré-formas ou na alimentação contínua de resíduos. Realizados os protótipos seguindo as metodologias acima descritas, urge verificar se as propriedades dos perfis híbridos correspondem às expectativas inicialmente neles depositadas, através de testes destrutivos e não-destrutivos. Assim, foram realizados testes à tracção, à compressão e à flexão, no intuito de verificar os ganhos conseguidos e poder analisar o valor-acrescentado trazido por estes novos perfis em termos estruturais. Estes valores, depois de devidamente validados, permitirão a sua inserção em bases de dados agregadas a programas de cálculo estrutural, que efectuam de forma automática o dimensionamento de estruturas baseadas em perfis desta natureza. Complementarmente, foram realizados testes de isolamento térmico e acústico, com vista a quantificar a melhoria conseguida nestas propriedades, extremamente importantes em determinados tipos de aplicações ligadas à construção civil e obras públicas.

Low cost synthesis of cathode and anode materials for lithium-ion batteries

Dans cette thèse, nous démontrons des travaux sur la synthèse à faible coût des matériaux de cathode et l'anode pour les piles lithium-ion. Pour les cathodes, nous avons utilisé des précurseurs à faible coût pour préparer LiFePO4 et LiFe0.3Mn0.7PO4 en utilisant une méthode hydrothermale. Tout d'abord, des matériaux composites (LiFePO4/C) ont été synthétisés à partir d'un précurseur de Fe2O3 par une procédé hydrothermique pour faire LiFePO4(OH) dans une première étape suivie d'une calcination rapide pour le revêtement de carbone. Deuxièmement, LiFePO4 avec une bonne cristallinité et une grande pureté a été synthétisé en une seule étape, avec Fe2O3 par voie hydrothermale. Troisièmement, LiFe0.3Mn0.7PO4 a été préparé en utilisant Fe2O3 et MnO comme des précurseurs de bas coûts au sein d'une méthode hydrothermale synthétique. Pour les matériaux d'anode, nous avons nos efforts concentré sur un matériau d'anode à faible coût α-Fe2O3 avec deux types de synthèse hydrothermales, une a base de micro-ondes (MAH) l’autre plus conventionnelles (CH). La nouveauté de cette thèse est que pour la première fois le LiFePO4 a été préparé par une méthode hydrothermale en utilisant un précurseur Fe3+ (Fe2O3). Le Fe2O3 est un précurseur à faible coût et en combinant ses coûts avec les conditions de synthèse à basse température nous avons réalisé une réduction considérable des coûts de production pour le LiFePO4, menant ainsi à une meilleure commercialisation du LiFePO4 comme matériaux de cathode dans les piles lithium-ion. Par cette méthode de préparation, le LiFePO4/C procure une capacité de décharge et une stabilité de cycle accrue par rapport une synthétisation par la méthode à l'état solide pour les mêmes précurseurs Les résultats sont résumés dans deux articles qui ont été récemment soumis dans des revues scientifiques.