Hybrid titanium-CFRP laminates for high-performance bolted joints

This paper presents an experimental and numerical investigation of the mechanical response of bolted joints manufactured using new hybrid composite laminates based on the substitution of CFRP plies with titanium plies. The local hybridization of the material is proposed to increase the efficiency of the bolted joints in CFRP structures. Two modeling strategies, based on non-linear finite element methods, are proposed for the analysis of the bolt-bearing and transition regions of the hybrid laminates. The bolt-bearing region is simulated using a three-dimensional finite element model that predicts ply failure mechanisms, whereas the free-edge of the transition region is simulated using plane stress and cohesive elements. The numerical and experimental results indicate that the use of hybrid composites can drastically increase the strength of CFRP bolted joints and therefore increase the efficiency of this type of connection. In addition, the numerical models proposed are able to predict the failure mechanisms and the strength of hybrid composite laminates with a good accuracy

Numerical modelling of multi-directional thin-ply carbon/glass hybrid composites with open holes under tension

Many researchers have used continuum damage mechanics for modelling damage in standard composites. This approach is intrinsically suitable for modelling the progress of damage modes spread over the specimen, which has been widely reported in pseudo-ductile hybrid composites. To the authors' best knowledge, this paper is the first numerical model based on continuum damage mechanics proposed for pseudo-ductile hybrid composites. The proposed constitutive model uses a thermodynamically consistent approach to compute the damage progression in the material. Experimental stress-strain curves and the failure pattern of carbon/glass hybrid lay-ups with gradual failure taken from the literature are compared against the numerical results to validate the model. The model provides a mesh-independent solution with a good prediction of the damage sequence and the overall stress-strain curves of the notched samples. A good correlation in size, location and type of damage mechanism was found between numerical and experimental results. This study indicates that the proposed model can provide a good prediction of the onset and propagation of the damage in notched hybrid composite laminates

Exploiting the benefits of multi-scale analysis in reliability analysis for composite structures

This paper investigates two critical issues, namely propagation of multi-scale uncertainty, and selection of failure criteria, related to reliability analysis of composites by using multi-scale methods. Due to the multi-scale architecture of composites, uncertainties exist in both microscale and macroscale parameters. It is necessary, therefore, to consider random variables at various length scales to ensure accurate estimates of the reliability of composites. Three types of homogenization methods, namely rule of mixtures, Mori–Tanaka and computational homogenization, are adopted to link these two scales, and to propagate uncertainty from micro to macro scales. By integrating these homogenization methods with the stochastic finite element method and structural reliability methods, the reliability of composites can be investigated with a limit state function based on a chosen failure criterion. This multi-scale reliability analysis procedure has been applied to analyse laminated fibre reinforced composites made of AS4/3501 carbon/epoxy. Firstly, a comparative study has been conducted to evaluate the performance of the assumed homogenization methods for the reliability of composites, and to identify advantages compared with a single scale analysis. The results show that multi-scale analysis can provide more accurate reliability estimates. Secondly, several popularly used failure criteria for composites have been compared using multi-scale reliability analysis

Modelización constitutiva y computacional del daño y la fractura de materiales compuestos

En el trabajo se definen modelos constitutivos que permiten reproducir el proceso de fallo de estructuras de materiales compuestos en distintas escalas bajo cargas estáticas. Se define un modelo constitutivo para determinar la respuesta de estructuras de materiales compuestos mediante la teoría de laminados. El modelo es validado mediante un programa de ensayos experimentales con probetas con un agujero central geométricamente similares. Se muestra la capacidad del modelo de detectar el efecto tamaño.Se define un modelo constitutivo para materiales transversalmente isótropos bajo estados tridimensionales de tensión. El modelo se valida analizando numéricamente el proceso de agrietamiento de la matriz. Finalmente se desarrolla un modelo analítico para determinar el agrietamiento de la matriz y la delaminación entre las capas.In this contribution a set of constitutive models are defined to reproduce the damage processes that takes place in laminated composites until failure at different scales under static loads.A damage model is defined to determine the structural response of composite structures by means of laminated theory. The validation of this model is done by comparing the numerical results with an experimental program on open hole test specimens. The ability of the model to reproduce the size effect in laminated composite is demostrated.A damage model for a transversely isotropic material under tridimentional stress states is defined. It is numerically validated analysing the process of matrix cracking in multidirectional composites.Finally an analytical model is defined that describes the onset and evolution of matrix cracking and delamination

Characterization of Interlaminar Friction during the Forming Processes of High-Performance Thermoplastic Composites

Friction is a pivotal factor influencing wrinkle formation in composite material shaping processes, particularly in novel thermoplastic composites like polyetheretherketone (PEEK) and low-melting polyaryletherketone (LM-PAEK) matrices reinforced with unidirectional carbon fibers. The aerospace sector lacks comprehensive data on the behavior of these materials under forming conditions, motivating this study’s objective to characterize the interlaminar friction of such high-performance thermoplastic composites across diverse temperatures and forming parameters. Differential scanning calorimetry (DSC) and dynamic mechanical analysis (DMA) were employed to analyze the thermomechanical behaviors of PEEK and LM-PAEK. These data guided friction tests covering room-to-forming temperatures. Horizontal pull-out fixed-plies tests were conducted to determine the friction coefficient and shear stress dependency concerning temperature, pressure, and pulling rate. Below the melting point, both materials adhered to Coulomb’s law for friction behavior. However, above the melting temperature, PEEK’s friction decreased while LM-PAEK’s friction increased with rising temperatures. These findings highlight the distinct responses of these materials to temperature variations, pulling rates, and pressures, emphasizing the need for further research on friction characterization around glass transition and melting temperatures to enhance our understanding of this phenomenon