The construction of high-performance vessels like the F50 catamaran has traditionally prioritized advanced composite materials and performance-driven design. However, there is a growing need to incorporate sustainable materials and practices, with their performance in marine applications remaining relatively unknown. This study aims to address this gap by investigating the feasibility of using flax laminates as an environmentally friendly alternative for frequently damaged components, specifically the stern extension.Mechanical testing of flax laminates revealed lower stiffness per fiber areal weight compared to literature values and supplier data sheets, primarily attributed to moisture uptake in the flax material. These findings highlight the significance of considering real-world environmental conditions and specific application requirements when evaluating the mechanical properties of flax composites. Despite the mechanical challenges, environmental analysis demonstrated that the flax alternative for the stern extension offers promising benefits. It exhibits a carbon-positive characteristic, resulting in lower energy consumption during production, and comparable waste production to the original carbon fiber extension. However, it is important to note that these advantages are based on idealized theoretical data, and further optimization is required to address variations in resin usage and the strength of the cured composite.To address the weight discrepancies among the fleet, currently rectified by corrector weights, a practical solution is proposed utilizing flax composite layups. Selective implementation of the flax stern extension on the lightest one-third of the fleet can effectively balance weight distribution without compromising overall yacht performance. This strategy allows SailGP to incorporate sustainable materials while maintaining uniformity and performance across all participating yachts. By considering the environmental impact and structural considerations, this study provides valuable insights for the development of sustainable marine composites and encourages further research in optimizing the performance and reliability of flax-based laminates in marine applications. / Vid konstruktion av högpresterande segelbåtar som F50-katamaranen har man traditionellt prioriterat avancerade kompositmaterial och prestandadriven design. Det finns ett växande önskemål av att införliva hållbara material och metoder i dessa båtar men materialens prestanda i marina applikationer är relativt okända. Denna studie syftar till att öka kunskapen genom att undersöka möjligheten att använda linfiberbaserade laminat som ett miljövänligt alternativ för komponenter som ofta skadas. Specifikt studeras en förlängning av akterspegeln som fungerar som ett lock runt roderinfästningen.Mekanisk provning av linbaserade laminat visade lägre styvhet per fiberytvikt jämfört med värden från litteraturen och leverantörsdatablad, främst tillskrivet fuktupptag i linfibrerna. Dessa resultat understryker betydelsen av att beakta verkliga miljöförhållanden och specifika tillämpningskrav när man utvärderar de mekaniska egenskaperna hos linkompositer. Trots de mekaniska utmaningarna visade miljöanalyser att linalternativet för akterförlängningen erbjuder lovande fördelar. Den ger lägre koldioxidutsläpp genom lägre energiförbrukning under produktionen och ungefär samma avfallsproduktion jämfört med den ursprungliga kolfiberförlängningen. Det är emellertid viktigt att notera att dessa fördelar är baserade på idealiserade teoretiska data, och ytterligare optimering krävs för att hantera variationer i hartsanvändning och styrkan hos den härdade kompositen.För att komma till rätta med viktskillnader mellan olika båtar, som för närvarande korrigeras med korrigeringsvikter, föreslås en praktisk lösning med användning av linkompositlaminat. Selektiv implementering av akterförlängningar av lin på den lättaste tredjedelen av flottan kan bidra till att balansera ut viktskillnader utan att påverka den totala yachtprestandan. Denna strategi gör det möjligt för SailGP att införliva hållbara material samtidigt som enhetlighet och prestanda bibehålls för alla deltagande yachter. Genom att ta hänsyn till miljöpåverkan och strukturella överväganden ger denna studie värdefulla insikter för utvecklingen av hållbara marina kompositer och uppmuntrar till ytterligare forskning för att optimera prestanda och tillförlitlighet hos linbaserade laminat i marina applikationer.

Diversos critérios de tenacidade à fratura translaminar dinâmica foram determinados para o laminado híbrido metal-fibra TiGra, empregando-se conceitos e metodologias da Mecânica da Fratura Elástica Linear MFEL (fator-K) e da Mecânica da Fratura Elasto-Plástica MFEP (integral-J). Verificou-se que as tenacidades de iniciação elasto-plástica, Jid, e de carga máxima, Jmd, do TiGra são controladas pelo desenvolvimento, ou supressão de delaminações. Os resultados indicaram que o emprego deste material se justifica mais pela sua resistência à propagação de danos (caracterizada por Jmd) do que à iniciação da fratura dinâmica (por Jid). De modo geral, os requisitos de validade de Jid como verdadeira propriedade do material (JId) foram satisfeitos, embora para Jmd boa parte das restrições quanto ao tamanho mínimo do corpo-de-prova tenha sido violada. Mais freqüentemente, velocidades mais rápidas de impacto beneficiaram as tenacidades-J do TiGra, enquanto que temperaturas mais elevadas afetaram negativamente estas propriedades. Quanto à MFEL, a tenacidade KJd do TiGra foi beneficiada pelo incremento na taxa de carregamento sob temperaturas mais elevadas, enquanto que a tenacidade Kid foi negativamente afetada pela taxa de deformação em todas as temperaturas avaliadas. Temperaturas mais altas também degradaram as propriedades de tenacidade-K do TiGra. Em oposição às tenacidades-J, os critérios KJd e Kid não satisfizeram em absoluto os mais exigentes critérios de contenção de plasticidade estabelecidos pela MFEL, se comparados aos propostos pela MFEP. Por fim, o desempenho mecânico do laminado TiGra foi severamente comprometido quando do cômputo da densidade específica para a determinação das tenacidades J e K por unidade de massa, sendo nesta ocasião o laminado híbrido facilmente superado por vários laminados convencionais da classe dos Carbono-Epóxi. / Several dynamic translaminar fracture toughness criteria have been determined for TiGr hybrid fiber-metal laminate through Linear Elastic (K-factor) and Elastic-Plastic (J-integral) Fracture Mechanics (LEFM and EPFM, respectively) concepts and methodologies. Instrumented Charpy impact testing was carried out over a wide range of temperatures under two loading rates. It has been discovered that the elastic-plastic initiation toughness, Jid, and the toughness at maximum load, Jmd, of TiGr are controlled by either delamination favoring or suppression. Impact tests revealed that the in-service use of TiGr must rely on its resistance to dynamic fracture propagation (as characterized by Jmd) rather than on fracture initiation (by Jid). In a broad sense, the requirements for Jid data validity as a material property (JId) were fulfilled, whereas many restrictive demands in regard to the minimum testpiece size were violated by the Jmd criterion. Generally, higher impact velocities were beneficial to TiGrs J-toughnesses, inasmuch as higher temperatures impaired these properties. Regarding the LEFM approach, KJd toughness of TiGr laminate was imparted by faster impacts at higher temperatures, whilst the strain rate negatively influenced the Kid toughness over the whole temperature range tested. Higher temperatures also degraded the K-toughness properties of TiGr hybrid laminate. Differently from J-toughnesses values, the KJd e Kid criteria did not satisfy at all the more stringent criteria set forth by the LEFM approach with regard to plastic constraint, as compared to those established by EPFM. Finally, the mechanical performance of TiGr laminate was overwhelmingly compromised as the materials specific gravity was taken in account to obtain K and J toughness values by unit weight, so that TiGr was by far exceeded in this regard by conventional Carbon/Epoxy composite laminates.

Composite laminates are an important subject of modern technology and engineering. The most common mode of failure in these materials is probably interlaminar fracture (delamination). Delamination growth under applied fatigue loads usually leads to structural integrity loss of the composite laminate, and hence its catastrophic failure. It is known that several parameters can affect the fatigue fracture performance of laminates. These include the constituent material properties, composite geometry, fatigue load variables or environmental factors. The knowledge about effects of these parameters on fatigue delamination growth can lead to a better understanding of composite fatigue fracture behaviour. Effects of some of these parameters can be elucidated by undertaking appropriate sensitivity analysis combined with the finite element method (FEM) and related software. The purpose of this work was three-fold. The first goal was the elaboration and computational implementation of FEM-based numerical strategies for the sensitivity analysis of interface fatigue crack propagation in elastic composite laminates. The second goal of this work was the numerical determination and investigation of displacement and stress fields near the crack tip, contact pressures along crack surfaces, mixed mode angle, energy release rate and the number of cumulative fatigue cycles. The third aim of the present study was to use the developed strategies to evaluate numerically the sensitivity gradients of the total energy release rate and fatigue life with respect to design variables of the curved boron/epoxy-aluminium (B/Ep-Al) composite laminate in two different material configurations under cyclic shear of constant amplitude. This study provided novel strategies for undertaking sensitivity analysis of the delamination growth under fatigue loads for elastic composite laminates using the package ANSYS. The numerical results of the work shed more light on mechanisms of interfacial crack propagation under cyclic shear in the case of a curved B/Ep-Al composite laminate. Moreover, the outcome of the sensitivity gradients demonstrated some advantages for using the sensitivity analysis to pinpoint directions for the optimisation of fatigue fracture performance of elastic laminates. The strategies proposed in this work can be used to study the sensitivity of the interface fatigue crack propagation in other elastic laminates, if the crack propagates at the interface between the elastic and isotropic components. However, the strategies can be potentially extended to composites with interfacial cracks propagating between two non-isotropic constituents under a constant amplitude fatigue load. Finally, the strategies can also be used to undertake the sensitivity analysis of composite fatigue life with respect to variables of fatigue load.

Les nouveaux renforts NCF (Non Crimp Fabrics) sont adaptés aux procédés RTM (Resin Transfer Moulding) ou RIM (Resin Infusion Moulding) et permettent d'élaborer des structures aéronautiques complexes et de grande taille. Cependant, la présence de la couture peut conduire à une morphologie spécifique hétérogène du matériau avec un réseau 3D de zones riches en résine. Ces dernières, sous cycles de vieillissement hygrothermiques, sont à l'origine d'un état spécifique de fissuration. Ainsi, le présent travail se concentre sur la caractérisation morphologique et la fissuration d'une famille particulière des NCF - NC2® (Non Crimp New Concept), soumis au vieillissement hygrothermique cyclique. Pour cela, des cycles accélérés de vieillissement sont définis, diverses méthodes de caractérisation sont utilisées et différentes variables représentatives sont introduites. Au sujet de la morphologie du matériau, une hétérogénéité multi-échelles a été visualisée en surface et dans l'épaisseur en effectuant des coupes sous microscope 2D et de la reconstruction volumique sous tomographie 3D à RX. En ce qui concerne la fissuration hygrothermique, son initiation et son développement ainsi que sa morphologie ont été étudiés. L'influence de la morphologie et des paramètres de chargement au cours des cycles a été identifiée. De plus, afin de maîtriser le comportement des zones riches en résine, un couplage thermique/hygrothermique-mécanique à différents états de vieillissement du matériau a été décrit finement par des mesures de champs. Enfin, la tenue mécanique du matériau vieilli a été étudiée.

In last decades, there has been a relevant growth in the application of composite materials reinforced by fibers in the several industries, especially the aeronautical, automotive, construction and offshore structures segments. How the composites exhibit relationships stiffness/weight and resistance/high weight, and other interesting features compared with other materials, they have been increasingly used to replace conventional materials. The present work has as objective to develop a study about laminated polymeric composite tubes subjected to thermomechanical loads. The laminae are composed of polymeric matrix involving unidirectional long fiber reinforcement. The walls of the studied tubes present various lamination schemes and different constituent materials. The analyses are set by analytical formulations that permits obtaining the displacements, stresses and strains, as well as verification failures in the laminae. Different empirical and semi-empirical analytical models are used for failure analyses. Effects of thermomechanical loads, such as internal pressure, bending, and temperature changes are considered. The analyzed cases consist of tubes with walls comprised of several layers with different directions of fibers, some including laminae sand impregnated with resin. The results are also compared with other available in the literature. It is verified that the Tsai-Wu criterion provides superior results to the other two failure models used in the work, especially for angles greater than 50°. Moreover, this criterion obtained an inconsistent result in the analysis of the temperature effects for the laminae [+55°/−55°]2. / Fundação de Amparo a Pesquisa do Estado de Alagoas / Nas últimas décadas, houve um grande crescimento na aplicação de materiais compósitos reforçados por fibras em diversos setores, com destaque para os segmentos aeronáutico, automotivo, construção civil e de estruturas offshore. Como os referidos compósitos apresentam relações rigidez/peso e resistência/peso elevadas, além de outras características interessantes, em comparação com outros materiais, eles têm sido cada vez mais utilizados em substituição aos materiais convencionais. O presente trabalho tem como objetivo o desenvolvimento de um estudo sobre tubos de materiais compósitos poliméricos laminados submetidos a cargas termomecânicas. As lâminas são constituídas por uma matriz polimérica envolvendo fibras unidirecionais longas de reforço. As paredes dos tubos estudadas apresentam diferentes esquemas de laminação, podendo ser constituídas por diferentes materiais. As análises são feitas através de formulações analíticas que permitem a obtenção dos deslocamentos, tensões e deformações, assim como a verificação de falhas nas lâminas. Para a análise de falhas são empregados diferentes modelos analíticos empíricos e semiempíricos. Efeitos de cargas termomecânicas, tais como pressão interna, flexão e de variação de temperatura são considerados. Os casos analisados consistem de tubos com paredes constituídas por várias camadas com diferentes direções de fibras, alguns incluindo lâminas de areia impregnada com resina. Os resultados encontrados também são comparados com outros disponíveis na literatura. Verifica-se que o critério de Tsai-Wu fornece resultados superiores aos dos outros dois modelos de falha utilizados no trabalho, principalmente para ângulos superiores a 50°. Além disso, esse critério obteve resultado inconsistente na análise dos efeitos de temperatura para o laminado [+55°/−55°]2.

Diversos critérios de tenacidade à fratura translaminar dinâmica foram determinados para o laminado híbrido metal-fibra TiGra, empregando-se conceitos e metodologias da Mecânica da Fratura Elástica Linear MFEL (fator-K) e da Mecânica da Fratura Elasto-Plástica MFEP (integral-J). Verificou-se que as tenacidades de iniciação elasto-plástica, Jid, e de carga máxima, Jmd, do TiGra são controladas pelo desenvolvimento, ou supressão de delaminações. Os resultados indicaram que o emprego deste material se justifica mais pela sua resistência à propagação de danos (caracterizada por Jmd) do que à iniciação da fratura dinâmica (por Jid). De modo geral, os requisitos de validade de Jid como verdadeira propriedade do material (JId) foram satisfeitos, embora para Jmd boa parte das restrições quanto ao tamanho mínimo do corpo-de-prova tenha sido violada. Mais freqüentemente, velocidades mais rápidas de impacto beneficiaram as tenacidades-J do TiGra, enquanto que temperaturas mais elevadas afetaram negativamente estas propriedades. Quanto à MFEL, a tenacidade KJd do TiGra foi beneficiada pelo incremento na taxa de carregamento sob temperaturas mais elevadas, enquanto que a tenacidade Kid foi negativamente afetada pela taxa de deformação em todas as temperaturas avaliadas. Temperaturas mais altas também degradaram as propriedades de tenacidade-K do TiGra. Em oposição às tenacidades-J, os critérios KJd e Kid não satisfizeram em absoluto os mais exigentes critérios de contenção de plasticidade estabelecidos pela MFEL, se comparados aos propostos pela MFEP. Por fim, o desempenho mecânico do laminado TiGra foi severamente comprometido quando do cômputo da densidade específica para a determinação das tenacidades J e K por unidade de massa, sendo nesta ocasião o laminado híbrido facilmente superado por vários laminados convencionais da classe dos Carbono-Epóxi. / Several dynamic translaminar fracture toughness criteria have been determined for TiGr hybrid fiber-metal laminate through Linear Elastic (K-factor) and Elastic-Plastic (J-integral) Fracture Mechanics (LEFM and EPFM, respectively) concepts and methodologies. Instrumented Charpy impact testing was carried out over a wide range of temperatures under two loading rates. It has been discovered that the elastic-plastic initiation toughness, Jid, and the toughness at maximum load, Jmd, of TiGr are controlled by either delamination favoring or suppression. Impact tests revealed that the in-service use of TiGr must rely on its resistance to dynamic fracture propagation (as characterized by Jmd) rather than on fracture initiation (by Jid). In a broad sense, the requirements for Jid data validity as a material property (JId) were fulfilled, whereas many restrictive demands in regard to the minimum testpiece size were violated by the Jmd criterion. Generally, higher impact velocities were beneficial to TiGrs J-toughnesses, inasmuch as higher temperatures impaired these properties. Regarding the LEFM approach, KJd toughness of TiGr laminate was imparted by faster impacts at higher temperatures, whilst the strain rate negatively influenced the Kid toughness over the whole temperature range tested. Higher temperatures also degraded the K-toughness properties of TiGr hybrid laminate. Differently from J-toughnesses values, the KJd e Kid criteria did not satisfy at all the more stringent criteria set forth by the LEFM approach with regard to plastic constraint, as compared to those established by EPFM. Finally, the mechanical performance of TiGr laminate was overwhelmingly compromised as the materials specific gravity was taken in account to obtain K and J toughness values by unit weight, so that TiGr was by far exceeded in this regard by conventional Carbon/Epoxy composite laminates.

Cette thèse est une contribution à la compréhension du comportement des composites carbone-époxy en compression par l’étude de l’influence des constituants (fibres et matrices). L’incidence d’un chargement mécanique d’amplitude constante ou variable sur la durabilité est étudiée et un modèle numérique permettant la prédiction de la résistance résiduelle est proposé. Une première partie des travaux s’intéresse aux mécanismes spécifiques engagés dans la résistance en compression. Un modèle analytique est retenu pour une confrontation expérimentale. Ce modèle propose de considérer d’une part le micro-flambage de la fibre comme contenu par le comportement en cisaillement de la matrice (Budiansky et Fleck, 1993). En complément, une partie supplémentaire de structure considérant, entre autres, l’influence du gradient de déformation induit dans une sollicitation en flexion 4 points est étudiée (Grandidier, 2002). Afin de valider la pertinence du modèle, une campagne expérimentale est menée sur six matrices époxy différentes (de fragile à ductile) dans des empilements stratifiés monolithiques identiques réalisés en cuisson autoclave. Ces résultats ont permis de valider la capacité du modèle à prédire l’influence de la rigidité de la matrice sur la résistance en compression. Le partie micro-flambage est validée pour la prise en compte de la matrice. La partie effet de structure (gradient ici) est validée par une comparaison avec des résultats supplémentaires obtenus sur des éprouvettes sandwich sollicitées en flexion. Ces dernières éprouvettes ont fait l’objet d’une conception spécifique afin de favoriser la rupture en compression pure (sans gradient de déformation). Une seconde partie est consacrée à l’étude de la durabilité en compression. Une campagne expérimentale d’essais de fatigue est menée en flexion 4 points sur les éprouvettes sandwich précédemment conçues. Les essais sont conduits à une fréquence de 10 Hz et différents rapports de charge dans une optique de dégager l’évolution de la résistance résiduelle. Un modèle numérique de changement d’échelles (stratifié, plis, constituants) est parallèlement développé, basé sur la dégradation et la plasticité de la matrice. On fait l’hypothèse de simplicité thermo-rhéologique de la matrice pour établir des courbes de maitresses à partir d’une série d’essais identifiés (fluage, relaxation, fatigue…). On utilise les propriétés résiduelles du pli (rigidité, résistance) pour estimer un indicateur d’endommagement. Ce dommage est répercuté dans les propriétés de la matrice au moyen d’une loi de dégradation linéaire. Une loi de cumul de dommage de type Miner est alors introduite pour tenir compte de la variabilité des chargements appliqués. Un solveur micro- mécanique est développé pour extraire le comportement non-linéaire du pli en cisaillement tenant compte de la dégradation. Ce comportement est paramétré par une loi de Ramberg-Osgood utilisée dans le modèle analytique validé précédemment. Les travaux des deux parties permettent donc la mise en place d’un outil de prédiction de la résistance résiduelle des plis sollicités dans un chargement biaxial plan, avec en particulier le traitement de la compression / This PhD dissertation is a contribution to the modelling of Carbon-Fiber-Epoxy-Polymer laminates, undergoing specifically compression loadings, according to components. The aim is to build a design tool for composites structures taking into account this compression specificity for dimensioning racing yachts parts (masts, daggerboards, foils), which is the expertise of HDS/GSea-Design, the company associated to this work. Emphasis was put on the influence of linear or non-linear properties of each phase by varying the type of fibre (from high stiffness to high strength) and the type of matrix (from brittle to ductile). The effect of a mechanical loading, static, constant (creep, relaxation) or variable (fatigue) on durability is studied and a numerical model for predicting the residual strength is proposed. The first part of this work deals with the mechanisms involved in compressive strength. An analytical model is used for an experimental validation. It considers a contribution linked to the micro-buckling of the fibre as contained by the shear behaviour of the matrix (Budiansky et Fleck [1993]). It considers also a contribution of the deformation gradient induced for instance in a bending loading (Gardin et al. [2002]). To validate this model, an experimental campaign was conducted on six different epoxy matrices (from brittle to ductile) on identical monolithic stackings processed in autoclave. The results allowed the validation of the model capability to predict the influence of the matrix stiffness on the compressive strength of unidirectional laminas. Taking into account the matrix behaviour validates the micro-buckling contribution. Regarding the deformation gradient contribution, it is validated through a comparison using additional experimental results on sandwich samples in bending. The latter samples were specifically designed to favour a pure compression fracture (without any deformation gradient). The second part examines durability in compression. Another experimental campaign with fatigue tests was conducted with four points bending tests on the same sandwich samples. Experiments were carried out at 10 Hz and different load ratios were used to study their influence on the compressive residual strength. A numerical model involving different scales (laminate, laminas, fibres and matrix) is developed in parallel (Huang et al. [2012a]), based on the degradation and the plasticity of the matrix. The assumption of thermo-rheological simplicity of the matrix is made to build master curves from dedicated experiments (creep, relaxation). We then use the residual properties (stiffness, strength) of the ply to estimate a damage level. This latter parameter is used to modify the elastic stiffness of the matrix with a linear law. A Miner-type cumulative law is used in fatigue to take into account the different possible loadings. A micro-mechanical solver is developed to extract the non-linear shear behaviour of the ply accounting for this degradation. This behaviour is described by a Ramberg-Osgood law used in the analytical model described in the first part of this work. The joint contributions of these two parts allowed us to program a numerical tool for predicting the residual strength of plies undergoing a biaxial in- plane loading, being monotonous, constant or with a variable amplitude, with emphasis on the particular case of compression loading.

Abstract The objective of this study was a values evaluation of fracture toughness of fiber-metal laminates (FML) compounded from carbon fibers in epoxy matrix and aluminium plates of lay-up 6/5. Samples with unidirectional and bidirectional orientation were tested experimentally. In the case of unidirectionally oriented samples an effect of moisture absorption to epoxy matrix on the values of fracture toughness was reviewed. A fracture toughness calculation was realized by COD method firstly. A bigger pop-ins in F – COD diagram as critical moments for "delta"c evaluation were considered; it was determined by 5% tangential line. It was found out, that results of this measurement weren’t in agreement with plane deformation condition and for this the results couldn’t be rated as fracture toughness "delta"Ic. A method of J integral for fracture toughness evaluation was used consequently. A test of elastic compliance changes before J integral calculation by all of samples was performed. Beginning of stable grow of crack was determined by this method. A critical forces Fc from beginnings were established, which were used for calculation of Jc. A functional dependence of elastic compliance on crack opening had specific waved shape before its linear (up to exponential) grow. It was observed in all cases. The critical forces Fc from the end of “wave” preceding the continual grow of compliance were determined. Equations stated in standards for J integral calculation were used, which are for metal materials normally used. Despite this was found out all of results of Jc were in good agreement with plane deformation condition and could be rated as fracture toughness JIc. In this study were found out these pieces of knowledge about fracture toughness of FML CARE: Unidirectional CARE had fracture toughness JIc about 76 kJ/m^2 and the same type but with bigger amount of absorbed moisture had JIc about 4 % higher. In this case negative moisture influences on CARE weren’t found. Bidirectional CARE had fracture toughness JIc about 31 kJ/m^2; it was about 65 % less then in the case of unidirectional CARE

The first part of the diploma thesis with name „Hybrid adhesive bonded joints of metals and composite materials“ comprise surface pretreatment review. There is also mentioned current review of adhesives for composite and aluminium adherends. The second part of the thesis is dedicated to lap hybrid joint shear strength tests. The effects of adherend thickness, overlap lenght and surface pretreatment on shear strength were investigated. Measured parameters of hybrid joints are proved with a FE analysis with enough accuracy. Conclusions could be used for optimum design of hybrid joint with aluminium and composite adherends.

<p>Multilayer polymer decorative films are showing a growing presence in the automotive industry, substituting conventional paint applications while maintaining similar aesthetic appeal. However for certain film constructions that have distinct layer properties, the polymer film laminates have shown to form wrinkles on application of heat during thermoforming. In this study, attempts were made to identify the factors influencing wrinkling and to predict the variation in the wrinkle parameters under changing forming conditions using existing theoretical models. A new modified thermoforming technique is proposed for producing thermoformed parts without wrinkles and thereby achieving a <em>Class A</em> finished surface.</p> / Master of Applied Science (MASc)