Quasi-isotropic (QI) structure for multi-layer fabric panel is believed to be a promising construction to manufacture soft body armour with higher efficiency of ballistic protection based on two hypotheses. The first one is that QI structure panel could involve more secondary yarns in transverse deformation, and the second one is that the more involvement of the secondary yarns could result in the corresponding increase of the energy absorption. However, recent study found that the advantage of QI panel made from Dyneema® woven fabrics was very limited over the aligned panel and potential reasons have not been identified for the lack of systematic studies. Accordingly, this research aims to provide explicit guidance on how to improve the QI structure panels for ballistic protection by studying the mechanisms of aligned and QI panels of multi-layer Dyneema® woven fabrics. The two hypotheses were tested to identify the mechanisms. The ballistic performance of the aligned and QI panels of 2-layer, 3-layer and 4-layer Dyneema® woven fabrics were experimentally investigated using a ballistic test apparatus and a panel clamping system to evaluate the energy absorption of specimens. In order to further study the response of the ballistic panel, a yarn-level Dyneema® woven fabric model was developed. The shear moduli of the yarn (G13 and G23) was found to be the most important elastic constants in simulating ballistic fabrics using orthogonal experiments in this study, and were identified to 0.27GPa and 0.80GPa. The model was agreeably validated by comparing the FE modelling results of multi-layer panels under ballistic impact with the experimental counterparts. Based on this validated model, the areas, shapes of the transverse deformation bases were specifically evaluated. The first hypothesis was verified that the areas of the deformation bases of the back layer fabrics in QI panels of 2-layer, 3-layer, and 4-layer fabric models were more than 10% larger than the areas of the corresponding parts in aligned panel models, especially at medium and late stages. Moreover, the increases of the areas were attributed to the more involvements of the secondary yarns in the deformation, and more circular shapes of the deformation bases of the fabrics in QI panels were identified by using a mathematic measurement method created in this study. The kinetic energy (KE) and total strain energy (IE) evolution of primary yarns and secondary yarns in two panels were further specified. It was found that altering the aligned panel to QI panel not only changed the energy absorption of secondary yarns, also significantly changed that of primary yarns. This indicated that the second hypothesis was not suitable for the cases of panels of the Dyneema® woven fabrics for the influence of the primary yarns after the panel structure changed were neglected. The reason of the alterations of the primary yarns was that the slip-off time or failure time of most primary yarns was changed. The morphology evolution of primary yarns in 2-layer aligned and QI panels were investigated and the results showed that the space between adjacent warp or weft primary yarns and the interactions between some primary yarns and the adjacent primary yarns in another layer significantly affected the slip-off time and failure time of most primary yarns. The influence of these two factors derived from the feature of woven fabrics, which was the crimp. In order to verify the new understanding of the QI ballistic panels from the numerical analysis, a non-crimp fabric, namely Dyneema® SB51, was used to investigate the ballistic performance of the aligned and QI panels. It was found that the energy taken by QI panels was approximately 25% higher than the energy taken by the corresponding aligned panels. This result verifies the analysis conclusion and paves the solid way for further investigation of QI structure panels made up of biaxial fabrics.

This research investigates composite tubes developed with hybrid preform manufacturing techniques of braiding and filament winding (FW). A quadriaxial braid-wound (QBW) preform [(±45°/0°/90°)2/(±45°/0°)] and a triaxial braided (TB60) preform [(±60°/0°)3] were developed. Quasi-isotropic (QI) fibre orientations were selected for both the lay-ups for comparison of mechanical properties. The large diameter of the tubes led to incomplete surface coverage with (±45°/0°)3 braided preforms (TB45). Circumferential distribution of multiple layers improved the coverage by reducing through the thickness resin pockets. Also addition of hoop winding improved the coverage and consolidated the braided preform. The use of braiding together with FW resulted in an improved fibre volume fraction. Also predicting surface coverage was a fundamental interest for a triaxial braided preform. An equation was proposed for cover factor estimation and was verified by using image analysis. Resin infusion of the preforms was carried out and composite tubes were fabricated. During resin infusion of braided preforms wrinkles were formed. A brief study on wrinkle formation was carried out and the reasons of wrinkle formation for braided tubes were identified based on existing literature. Longitudinal tensioning in conjunction with optimization of fibre amount in a layup and over-winding on braid was established to minimize wrinkle formation. This was primarily due to compaction of braided layers with hoop winding. Hence braid-winding has the additional advantage of manufacturing wrinkle free composite tubes. Finally composite tubes were tested under tension and torsion loads. One of the major findings was the effect of hoop winding on transverse deformation of the braid-wound tubes. As axial fibre percentage for QBW tube was less than that of TB45, the tensile strength was compromised. However presence of hoop winding resulted in lower transverse strain contributing to higher tensile modulus of QBW tubes along with lower Poisson's ratio. Although shear modulus of TB60 tube was exceptionally high for its fibre orientation, for QBW tubes, shear modulus was not significantly higher than that of other tubes. An aluminium tube was also tested for comparing the elastic properties of the QI tubes with those of an isotropic material. QBW tubes specific modulus was higher than that of the aluminium. The shear modulus of the QI and aluminium tubes was estimated by applying the theory for isotropic materials. In comparison to aluminium, for QBW tube the differences between estimated and actual shear modulus was higher. However QBW tube properties were in closer relation to those of the aluminium tube than TB60 tubes. Hence a QBW hybrid layup technique has the potential for manufacturing composite tubes without losing comparative composite material properties.

This study investigates the through-thickness behaviour of carbon/epoxy laminates. A through-thickness compression test regime was conducted utilising three specimen designs, which are waisted, hollow cylindrical and cubic specimens. An assessment and comparison of each specimen is given regarding their advantages and disadvantages in characterising the through-thickness response of [+45/-45/90/0]s quasi-isotropic AS4/8552 carbon/epoxy laminates. A finite element (FE) study of the three specimens is presented which results in specimen geometries that provided a macroscopically uniform stress response throughout the gauge length whilst also minimising other features such as stress concentrations. Further to the final geometries being presented, the method of manufacture for the laminate and machining processes for each of the specimens is given. A mesoscopic FE study is presented relating to the free-edge effects induced by through-thickness loading in quasi-isotropic laminates. The results presented show that free-edge effects will be present in the test specimens and will have a larger overall impact on the hollow cylindrical specimen. The free-edge effects also increase the stress concentrations present in the corners of the waisted and cubic specimens. Characteristic stress strain curves are presented for each specimen with strain data taken from post yield strain gauges attached to the specimens. The extracted initial Young's modulus Ez and Poisson's ratios vzx and vzy show a small variation between specimens. The strength values for the three specimens vary greatly with the waisted specimen being the strongest and cylindrical specimen the weakest, indicating that the chosen specimen geometry dominates failure. The experimental data will be used for test case 12 in the Second World Wide Failure Exercise (WWFE-II). A study is presented to predict the effective elastic properties of Z-pinned laminates. The materials under consideration are UD and [0/90]s cross-ply AS4/3501-6 carbon/epoxy laminates. Estimates on the effective properties are provided by two FE approaches and two analytical bounding approaches; namely Voigt and Reuss bounds and Walpole's bounding theory. The two FE approaches are based on extreme assumptions about the in-plane fibre volume fraction in the presence of Z-pins and provide a tight range of values in which the real result should lie. Furthermore, whilst the bounding methods are simple and in the case of Young's moduli produce very wide bounds the selection of the suitable bound result can lead to a good estimate in comparison with the FE data. Typically the best bounding method result for each elastic property is within 10% of the FE predictions.

The extensive industrialization and human expansion has caused environmental protection wildlife conservation to become paramount concerns of the 21st century. The ecosystems of oceans and seas have particularly been affected due to activities like oil spills and increased fishing. This has led to a growing interest in monitoring of the oceans and marine animals to detect signs of distress in aquatic species. However, acquisition of data from oceans to land has been a challenging and expensive task. The concept of Internet of Sea provides a solution to this data transfer between the ocean nodes, like animal tags or deployed floating transceivers, and our land Internet, and can potentially eliminate the need of expensive monitoring ships or underwater cables. The Internet of Sea is system that comprises of sensor nodes in the form of detachable marine animal tags as the data acquisition platforms and distributed floating transceivers as the intermedium nodes which then transfer the data to the base-stations located on lands. The data acquired by animal tags are first to be stored in the tag, and once the tag comes to the sea surface, the data is transferred to the nearby floating transceivers. The floating transceivers have multi- hopping capability so the data can be passed to the land base-stations through a small number of transceivers. Due to the specific geometric shapes and size constraints of the tag and floating transceivers, as well as the harsh ocean environment, novel integrated antennas are required for this type of system. In this thesis, we propose several antenna designs suitable for Internet of Sea applications. The first design is a quasi-isotropic Antenna in Package (AiP), operating in the Bluetooth band, which has been designed for semi-real-time monitoring. Secondly, a large frequency-ratio dual- band microstrip antenna array, working at Extended Global System for Mobile communications (E-GSM900), Long Range (LoRa), and Bluetooth bands, has been designed for large-area wireless communication. Lastly, a circularly polarized microstrip antenna array has also been designed for Global Positioning System (GPS). Throughout the work, the measured results are consistent with the design strategies and simulation results.

In the last few decades, there has been a shift to using more lightweight materials for the potential of fuel consumption reduction. In the Aerospace Industry, conventional metal structures are being replaced by advanced composite structures. The major advantage of an advanced composite structure is the huge reduction in the number of parts and joints required. Also composite materials provide better resistance to creep, corrosion, and fatigue. However, one cannot eliminate all the joints and attachments in an aircraft’s structure. Eliminating structural joints is impractical in present-day aircraft because of the requirements for inspection, manufacturing breaks, assembly and equipment access, and replacement of damaged structures. Currently, composite joints are overdesigned which leads to weight penalties. Understanding how to optimize the ultimate bearing strength of a composite joint by altering the cure cycle might be beneficial to the composite joint design process. This study investigates, through numerical and experimental analysis, the mechanical behavior of double shear joints. The first task is to test Aluminum double shear joint specimens inside the double shear joint fixture at a loading rate of 0.05 in./min. (quasi-static). The second task is to numerically model and validate the aluminum double shear joint specimen. The third task is to test the Unidirectional MTM 49 carbon fiber pre-preg double shear composite joint specimens with two different cure cycles and five different loading rates (0.05 in./min., 0.1 in./min., 1 in./min., 2 in./min. and 6 in./min.). The double shear composite joint specimens are made, using a heat press, with a quasi-isotropic laminate orientation of [0 0 +45 -45 +45 -45 90 90]s. The first cure cycle used is called the alternate cure cycle, which is Cytec’s MTM 49 Unidirectional Carbon Fiber pre-preg material cure cycle, and the second cure cycle used is called the datasheet cure cycle, which is Umeco's MTM 49 Unidirectional Carbon Fiber pre-preg material cure cycle. The recommended datasheet cure cycle and an alternate cure cycle are both compared to see how they affect the mechanical characteristics of the matrix along with the bearing stress. The fourth task is to adjust the Aluminum double shear joint numerical model for the double shear composite joint specimen. The numerical results for both the Aluminum and the composite specimens are in agreement with the experimental results. The theoretical in-plane material properties of the quasi-isotropic laminate were in agreement with the experimental results. One can see that at 0.05 in./min. and 0.1 in./min. (for both cure cycles) the composite double shear specimens carried more load compared to the higher loading rates of 1 in./min., 2 in./min. and 6 in./min. The tensile modulus of elasticity of an Aluminum sample is measured using a crosshead displacement, a strain gage and an extensometer. The crosshead displacement yielded very inaccurate results when compared to the strain gage and the extensometer.

Ce travail a pour but d'étudier la tolérance à l'impact de 3 stratifiés carbone/époxy soumis simultanément à différents types de chargements hygrothermiques et mécaniques. Ces stratifications présentant des caractéristiques mécaniques globales particulières d'isotropie, il s'agit ici de déterminer l'influence de la séquence d'empilement sur le développement de l'endommagement lors d'un impact. Dans un premier temps, la cinétique de vieillissement hygrothermique des trois stratifications est étudiée et analysée. Ensuite, leur tolérance à un unique impact ainsi qu'à des impacts répétés est évaluée. L'endommagement résultant de ces impacts est analysé par contrôle ultrasonore. La morphologie générale et l'amplitude de l'endommagement dans la profondeur des matériaux sont mises en relation avec les propriétés mécaniques et la séquence d'empilement spécifique à chaque stratifié. Dans un deuxième temps, l'influence combinée de plusieurs sollicitations est étudiée. Différents scénarii associant un vieillissement hygrothermique ainsi qu'un ou deux impacts sont mis en oeuvre. L'endommagement résultant est mis en rapport avec les temps relatifs de vieillissement et la position des impact durant le cycle de vieillissement. Ensuite, l'influence d'une précharge de traction sur la tolérance à l'impact est mise en évidence. Un montage spécifique a été conçu et fabriqué pour réaliser ces tests. Enfin, l'association d'un vieilllissement hygrothermique et d'une précharge de traction est abordée afin d'identifier la sollicitation la plus pénalisant en terme de tolérance et d'impact / This study examines impact damage processes in three types of CFRP composite materials simultaneously subjected to different hygrothermal and mechanical loading conditions. The composite structures tested are chosen for having particular global isotropic responses when loaded, the aim being to ascertain the exact influence of lay-up sequence on impact damage propagation. The work is presented in four main sections. Firstly by establishing hygrothermal ageing dynamics for the three composite structure types and their behaviour when impacted once or several times ; impact damage is measured and analysed using ultrasonic method. The extent and general morphology of the damage through the material thickness is correlated with mechanical properties and lay-up sequence specific to each material. Secondly the influence of simultaneous load combinations is examined. These include different durations of hygrothermal ageing associated with single or double impacts.The resulting damage incurred is analysed with respect to overall ageing time and time during the ageing cycle when the impact was applied. Thirdly the effect of tensile loading during impact on damage within the material was studied. This was achieved using a specially designed test apparatus that allows loading and impacting conditions to be independently modified. By associating a high-speed digital camera to film specimen impacts it is possible to evaluate a relationship between overall composite specimen stiffness and the impact damage. Finally, in order to identify the most unfavourable situation with regard to impact damage resistance an association between hygrothermal ageing and an applied tensile load is examined

L’assemblage des matériaux composites thermoplastiques tel que le PEEK est l’une des problématiques majeure de l’industrie aéronautique. Actuellement, différentes techniques sont développées pour assurer l’assemblage structural de ces matériaux, tels que : le soudage, le rivetage, le boulonnage et le collage. Les enjeux industriels majeurs sont principalement, à l’heure actuelle, la conception des structures simplifiées au maximum afin de réduire les coûts de production et la réduction des consommations énergétiques. A cet effet, l’industrie aéronautique fait fréquemment appel à l’assemblage par collage en raison de nombreux avantages qu’il offre (gain de poids, distribution régulière des contraintes, absence de trous) par rapport aux autres techniques existantes. Le PEEK (PolyEtherEtherKetone), est un matériau polymère semi-cristallin thermoplastique, à hautes performances. Ce matériau est souvent utilise dans l’industrie aéronautique principalement renforce par des fibres de carbone ou de verre. Cependant, du fait du niveau élevé de sa résistance chimique l’assemblage par collage du PEEK et de ses composites nécessitent des traitements de surfaces appropries et optimises. Or, afin d’obtenir un system collé à haute performance, la problématique scientifique et technique doit être concentrée sur la jonction entre les éléments à assembler. En effet, la qualité de cette jonction est de la plus haute importance car elle doit permettre un transfert optimal des contraintes thermomécaniques lorsque l’assemblage est soumis a ses conditions d'usage. Cette étude concerne donc, l’amélioration des propriétés mécaniques (monotones et cycliques) de l’assemblage par collage PEEK/PEEK. Dans cette optique, un traitement de surface simple de mise en œuvre est proposé. Ce traitement est le sablage, qui permet la modification topographique (morphologique) de surface. La compréhension des différents phénomènes d’interaction aux interfaces intervenant dans l’amélioration du comportement mécanique du joint de colle et qui s’inscrit dans la triptyque : « Rhéologie, Physico-chimie et topographie », est l’enjeu scientifique majeur dans cette thèse. Dans un premier temps, l’influence des paramètres du traitement tels que le temps de projection, la taille des particules, sur la morphologie de surface de différents matériaux à base de PEEK a été analysée, permettant ainsi d’établir la corrélation entre les paramètres morphologiques et les mécanismes de modification topographique de surface intervenant pendant le traitement de surface. L’un des facteurs clefs pour la compréhension des mécanismes d’interaction entre l’adhésif liquide et le substrat solide est la mouillabilité. L’analyse du comportement au mouillage en fonction des différents paramètres du traitement a été réalisée. La mouillabilité des surfaces traitées est fortement affectée par la rugosité de surface créée après ce traitement. La relation entre les paramètres morphologiques et la mouillabilité a été discutée. Enfin, l’influence des paramètres du traitement par sablage sur le comportement mécanique monotone et à long terme (essais de fatigue) sur la résistance du joint colle a été étudié à l’aide d’essais de cisaillement sur éprouvettes à simple recouvrement. Ceci a conduit, à la proposition de paramètres morphologiques surfaciques spécifiques pour l’optimisation du comportement mécanique du joint de colle des matériaux composites à matrice PEEK. / One of most problematic in the aeronautical industries is the structural joining of the high performance thermoplastic composites like PEEK composites. Actually, a lot of technologies are used for joining thermoplastic composites like welding, bolting, riveting, fastening and adhesive bonding. Due to the various advantages that characterize the adhesive bonding method, such an uniform stress distribution along the joint, weight‐light and cost reduction, makes this technique more desirable to join thermoplastic composites materials compared to the other joining techniques. PEEK (PolyEtherEtherKetone) is a semi‐crystalline thermoplastic material with high performance. This material is wildly used in aeronautical industries, principally, reinforced with carbon of glass fibres. However, its high chemical resistance makes the adhesive bonding of PEEK and its composites difficult and therefore an appropriate and optimised surface treatment is necessary. In the aim to obtain a bonded system with high performance, scientific and technical problematic should be focussed on the junction between adherents. Indeed, the quality of this junction is of utmost importance because it must allow optimum transfer of thermomechanical stresses when the assembly is subject to its terms of use. Though, at this time it is well known that thermoplastic composite materials are difficult to bond with‐out surface treatment. This study, therefore, relates to the improvement of mechanical properties (monotonic and cyclic) of the adhesive bonding system PEEK / PEEK. In this context, a surface treatment, easy to implement, is proposed. This surface treatment is sandblasting, which enables surface topographic (morphological) modifications. Understanding of various phenomena of interfaces interaction involved in the improvement of the mechanical behavior of the adhesive joint and is part of the triptych "Rheology, Physico‐chemistry and topography" is the major scientific challenge in this thesis. Initially, the influence of processing parameters such as the projection time, the particle size on surface morphology of various materials based on PEEK was analysed, thus allowing establishing the correlation between morphological parameters and modification mechanisms involved during surface treatment surface. One of the key factors for understanding the mechanisms of interaction between the liquid adhesive and the solid substrate is wettability. The analysis of the wetting behavior as a function of various parameters of the treatment was performed. The wettability of treated surfaces is strongly affected by surface roughness created after this treatment. The relationship between morphological parameters and wettability was discussed. Finally, the influence of sandblasting processing parameters on the mechanical behavior in monotoning and long‐term (fatigue tests) of the adhesive joint strength was studied, using single lap shear tests specimens. This has led to the proposal of specific surface morphological parameters for the optimization of the mechanical behavior of the adhesive joint of PEEK and its composites.