An extensive study of into the static loading response and low-velocity impact response of plain and stiffened CFRP panels was conducted. The study investigated the impact response of the CFRP panels over a range of impact energies that include incident kinetic energies sufficiently high to cause complete penetration of the panel by the impacting mass. Static tests were also conducted by driving a hemispherical-nosed indentor into the panel up to displacements that resulted in the complete penetration of the panel by the indentor. Results from these tests suggest that the static perforation energy could predict the impact perforation energy with reasonable accuracy. A lumped-parameter mass-spring-damper model that attempted to incorporate the effects of material damage to the panel response was developed. The model was found to be sufficiently accurate in predicting the response of thin panels to static and impact loads up to the critical delamination force threshold. Assessment of the damaged panels through Penetrant-Enhanced X-Ray methods led to the identification of damage transition energy thresholds that differentiate between changes in damage mechanism. The damage transition energy thresholds were found to be constant fractions of the impact perforation energy.

The strength of carbon fibres in unidirectional hybrid composites of glass and carbon fibres have been investigated. It has been shown that the strength distributions of bundles of carbon fibres impregnated with resin, both unsupported and in a hybrid, may be described by the Weibull model confirming earlier reports. The primary objective of this work has been to investigate the strength and the state of dispersion of the carbon component. Hybrid composites consisting of accurately aligned arrays of bundles in two and three dimensions have been fabricated and tested. It has been shown that the strength decreases when the bundle spacing is less than a critical distance but at very low spacings the strength begins to increase again. This observation is explained with reference to the fracture behaviour and the implications for practical composites are discussed. The hybrid composites exhibit a greater strength over impregnated bundles. An hypothesis is proposed to explain this phenomena which combines thermal effects with the constraining influence of the glass and the differences in the severity of flaws in hybrid bundles. The last two arguments result in a larger critical group of failed fibres being required in the hybrid before catastrophic failure occurs. The type of hybrid specimen tested in this work enables the fracture process in the composite to be followed closely. The investigation has in principle supported the model for composite strength proposed by Batdorf, the "critical i-plet" model. However, experimental evidence indicated that a slightly different fracture process to that proposed by Batdorf was operating. The significance of this fracture process with respect to the strength and the size effect in composites is discussed.

The interfacial micromechanics of both high modulus and low modulus carbon fibres have been investigated using Raman spectroscopy. The innovative step was to make low modulus carbon fibres more Raman active by coating them with SWNTs to act as as a strain sensor. Two types of SWNTs have been employed; namely HiPCO SWNTs and COOH SWNTs. Single fibre deformation tests were carried out and the Raman band shift rates with respect to fibre strain have been determined. Meanwhile, different SWNTs coating methods have been investigated. The method of adding COOH SWNTs into the silane layer and within a hot cured epoxy layer was found to generate the highest band shift rates. Furthermore, an investigation of the effect of SWNTs on the strength of the interface was also carried out. A coating of COOH SWNTs was found to significantly improve the interfacial shear strength. Micromechanical tests have been carried out and the stress transfer between the carbon fibres and an epoxy resin was monitored using three different model composite geometries; namely microdroplet-fibre, a film-fibre and a standard fragmentation approach. The result of interfacial shear stress determined from microdroplet-fibre method varied and was found to be highly dependent on the droplet size and shape; this gave the lowest values of interfacial shear stress (ISS). The method of film-fibre obtained an intermediate ISS value which is between that from the microdroplet model test and the fragmentation test. The standard fragmentation test using Raman technique gives the highest ISS and HiPCO SWNTs were found to be a better strain sensor without affecting the original interfacial properties.

Use of lightweight materials is an important part of reduction of fuel consumption by commercial aircraft. A considerable number of structural aircraft parts are therefore built of thin layers of epoxy pre-impregnated carbon fibres stacked to laminates. Manufacturing these by hand is costly and different methods of automation have therefore been developed. One cost-effective way of manufacturing is Automated Tape Lay-up of flat stacks followed by a Hot Drape Forming operation. A well-known problem in the industry within forming is fibre wrinkling, which can cause a serious strength knock down. The focus of this thesis has therefore been on understanding how and why wrinkles develop during forming of multi-layer stacks and, based on this, investigate different methods for process and material improvements. The work presented initially investigates the dependency between stacking sequence and wrinkle development. It is shown that wrinkle free forming can be obtained by changing the fibre stacking order. In the following investigation it is shown that the wrinkles cannot be entirely eliminated by local stiffening of the critical layers. In a, related study it is shown that different kinds of wrinkles develops during forming; wrinkles may be either due to global buckling of the entire lay-up or local compression of single layers. Global buckling is due to excessive material. Local compression occurs as the material shear during forming. The work presented leads to an understanding of the importance of making the beneficial neighbouring fibre layers interact during forming. One way to connect neighbouring layers is to tailor the interlayer properties. A study is presented that shows how local manipulation of interlayer properties may steer the multi-layered material into a different deformation mechanisms. The manipulation in this thesis is performed using Multi Wall Carbon Nano Tubes, thermoplastic veils or consolidation of thermoplastic toughener particle interlayers. / <p>QC 20160425</p>

No description available.

No description available.

The type and extent of surface oxidation of carbon fibres has been determined after electrochemically treating fibres in a variety of electrolyte solutions. The chemical and physical characteristics of these fibres have been evaluated using XPS, SEM, FTIR and UV spectroscopy. The fibres were anodically treated, both in a laboratory and in a commercial type cell. Fibres that have undergone commercial treatment were then incorporated into epoxy composites, the ILSSs of which were then measured. The extent of oxidation and type of surface functionality produced as a result of electrochemical treatment is shown to depend upon several factors, ie the nature of the electrolyte, the anodic potential, reaction time, the structure of the fibre surface, the pH of the electrolyte solution, and the electrolyte concentration. Surface nitrogen functionality is not produced as a result of polarising the fibres in nitric acid. It is produced, however, with treatments in solutions containing ammonium ions. The amount of surface nitrogen depends upon the concentration of these ammonium ions in the solution. In most cases, polarisations in salt solutions produce similar changes in the fibre surfaces as treatment in the acid alone. The presence of bicarbonate ions tend to inhibit fibre surface oxidation. In acidic solutions the fibres are shown to be extensively oxidised. Although the functionality of the oxide layer produced is very similar Ge. consisting of keto- and carboxyl/ester groups) after all the acidic treatments studied, the surface topography of the oxide layer produced is very different. In all cases this oxide layer is loosely bound to the bulk fibre. In general, as reaction time increases, oxidation of the fibre surfaces also increases. Surface oxidation also increases with potential. However at high potentials (-3V) and long reaction times (>15mins) the detected functionality of type 11 fibres decreases. This is thought to be due to the formation of gaseous products such as carbon dioxide. The reactivity of type I and type II fibre is shown to be different. The amount of carboxyl/ester functionality produced is far greater for type 11 fibres. It is concluded that carboxyl functionality is produced at the edge sites and keto-type functionality on the basal planes. The amount of oxidation decreases as the pH increases. In alkaline solutions carboxyl and alcohol groups are produced, (the former being in greater quantities). The physical mechanism of oxidation is also different. Instead of an overall oxide layer being produced (in acidic solutions), holes are produced in the fibre surfaces. These holes are thought to be areas of localised attack. It is also shown, using a small pilot plant, that both galvanostatic and. potentiostatic control of electrolysis are satisfactory in producing treated fibres, which when incorporated into resins form composites with a high ILSS. The ILSS of the composites produced are dependent neither upon the amount of surface oxygen present nor upon the number of carboxyl groups present.

No description available.

Fibre reinforced plastic (FRP) composites consist of two or more components combined to give a synergistic effect for a better performance in service. One of the phases comprises layers of fibrous material while the other phase comprises of a polymer matrix. In this project, carbon fibre pre-preg material was used. All materials contain imperfections. Materials constituents and manufacturing anomalies are the main causes of faults in FRP composites. The presence of voids in FRP composites is the most common defect. The aim of this project was to determine the influence of voids on the static and dynamic compressive properties of carbon fibre reinforced plastic (CFRP) composites. The influence of voids on fatigue life and failure behaviour were also investigated.

No description available.