Advanced Materials

Advanced Materials

These are some of the PhD programmes we can offer in this research field (please note that these refer to research projects, no studentships):

 

Functionally Graded Materials (FGM): New Configurations and Designs

 

Supervisor: Dr Jose L Curiel-Sosa

 

This investigation will focus on the relatively novel field of FGM. FGMs can be the answer to many problems associated to classical materials. Worldwide, industrial sectors are looking for multifunctional and safer materials for innovation and development of new technologies.

This reearch will help you to develop a combination of modelling and simulation skills in order to research the performance of FGM. This research will benefit from excellent computing facilities, expertise in computer-aided engineering (CA2M lab), the available experimental facilities including mechanical testing and 3D-printing manufacturing.

 

For further information please contact Dr Jose Curiel-Sosa (j.curiel-sosa@sheffield.ac.uk)

 

Simulation and Analysis of Damage for Failure Prediction on Advanced Composite Structures subjected to Impact Loading

 

Supervisors: Dr Jose L Curiel-Sosa, Dr V Phadnis

 

The development of new advanced composite materials offers plenty of possibilities to implement these new structures into highly strained components and applications. For example, fuselage made of GLARE (hybrid laminate compounded by alternated glass fibre plies and aluminium layers; used in Airbus A380 fuselage) or hybrid CRF and titanium aircraft engine blades. The design certification is strongly depending on the numerical simulations in order to reduce to a minimum the certification costs. Aircraft composites failure is characterized by different damage modes such as fibre kinking, fibre rupture, matrix cracking or delamination, which makes challenging to calculate an exact prediction of the failure process. However, novel available techniques are promising for the solution of such problems.

This investigation will help you to develop a combination of modelling and simulation skills in order to research the prediction of failure on modern composite structures. This research will benefit from excellent computing facilities, expertise in computer-aided engineering (CA2M lab), the available experimental facilities including mechanical testing and links with industry and with our Advanced Manufacturing Research Centre (AMRC) through our collaborative work.

 

For further information please contact Dr Jose Curiel-Sosa (j.curiel-sosa@sheffield.ac.uk)

 

Failure Analysis of Composite Airframes: Investigation and Predictive Modelling

 

Supervisor/s: Dr Jose L Curiel-Sosa

 

Composite airframe panels are subjected to extreme loads and impacts. Cracks can develop at microstructure at an early stage and then propagate due to fatigue. There is an ever growing interest in the design of safer composites for aviation. This PhD will aim to investigate on those mechanisms of failure and how to mitigate them.

This investigation will help you to develop a combination of research skills for analysis and prediction of failure on modern composite aircraft. This research will benefit from excellent computing facilities, expertise in computer-aided engineering (CA2M lab), the available experimental facilities and links with the new Boeing facilities at Sheffield and our Advanced Manufacturing Research Centre (AMRC) through our collaborative work.

For further information please contact Dr Jose Curiel-Sosa (j.curiel-sosa@sheffield.ac.uk)

 

Modelling of Compressive Transverse Cracking on Composite Laminates

 

Supervisor/s: Dr Jose L Curiel-Sosa

 

In analyses of failure in composite laminates, extended finite element analyses using Abaqus (or Ansys) might prove convenient for the prediction of transversal cracks on composite laminates subjected to compression. Cracks are represented as a strong discontinuity in the displacement field. Under compression cracks tend to be inclined within the layer mid-plane which can lead to failure where the outer plies are pushed out of the plane of the laminate and eventually buckle. In principle, it is possible to model the inclined crack plane with the Finite Element Method. The basic idea is that the direction into which stiffness recovery under compression takes place is altered for a crack that develops under compression. Only one layer of elements per ply might be used, which is typically done for reasons of computational efficiency. The project can also include simulations where in-plane shear is acting on the potential crack plane.

 

For further information please contact Dr Jose Curiel-Sosa (j.curiel-sosa@sheffield.ac.uk)

 

Simulating Composite Fracture by the Extended Finite Element Method

 

Supervisor/s: Dr Jose L Curiel-Sosa

 

In this project, three-dimensional analyses of fracture in composite laminates will be conducted. The aim is to investigate if the XFEM is capable to reproduce fracture in composites with a sufficient degree of accurateness in terms of energy release rates and stress intensity factors.

ABAQUS and XFEM MATLAB programs are available for the analyses. Extension of such program could be done in case of it was necessary. For instance, for the linkage of new material models or certain numerical features such as a new finite element.

 

For further information please contact Dr Jose Curiel-Sosa (j.curiel-sosa@sheffield.ac.uk)

 

Analysis of delamination in cross-ply laminates: energy release rates and cohesive zone modelling

 

Supervisor/s: Dr Jose L Curiel-Sosa

 

Identification of delamination is at the forefront of damage and fracture mechanics of composite laminates. In this project, predictive modelling and simulation will be carried out to assess delamination in cross-ply carbon fiber epoxy laminates.

 

For further information please contact Dr Jose Curiel-Sosa (j.curiel-sosa@sheffield.ac.uk)

 

Structural Integrity Finite Element Analyses of Formula I Composite Panels for Safer and Lighter Designs

 

Supervisor/s: Dr Jose L Curiel-Sosa

 

Formula 1 car composite panels are subjected to extreme loads. Cracks can develop at the composite microstructure at an early stage and then propagate due to fatigue which poses a serious hazard. A compromise between specific strength and safety of the composite structures is crucial for an optimal design. Different composite structures will be tested for optimisation of the best structural configuration in the terms of safety and specific strength. The final test would involve the whole Formula 1 chassis subjected to a typical loading scenario

 

For further information please contact Dr Jose Curiel-Sosa (j.curiel-sosa@sheffield.ac.uk)

 

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