A Midlands based UK University is seeking partners to join their consortium for the Eureka Multilateral Advanced Materials call. They are specifically interested in the utilisation of 4D x-ray visualisation to build an understanding of the sources of material inconsistency and failure. The are looking for aerospace composite companies that are interested in building aircraft structures from PEEK (Polyetheretherketone) and/or carbon fibre.
The UK University is interested in the definition and recording of an approach/process by which CT (computed tomography) scanning and analysis can be used to evaluate the time-dependent, 4D, development of in-process porosity of a composite structure during compression moulding. Enhanced characterisation of the nucleation and evolution of defects is critical to predicting structural integrity of the composite. A resolution of 1µm has been demonstrated appropriate to capture both primary damage events and key local events enabling multi-scale characterisation of damage mechanisms. This research is industrially relevant because the degree of porosity and associated crack propagation within a composite structure influences its mechanical properties, in particular its fatigue strength/performance. Composite materials, thermoplastics and thermosets) are used extensively within aircraft. By far the most significant advantage of composite materials is the potential for tailored anisotropic properties meaning a structure can be as strong and stiff as necessary whilst benefitting from improved structural weight and ultimately improved fuel efficiency. This is particularly relevant as the International Civil Aviation Organization (ICAO) has set the objective of maintaining global net CO2 emissions at 2020 levels through 'carbon neutral growth' and through compensation of emission growth above 2020 levels. The University's investigation will focus on Poly-Ether-Ether-Ketone (PEEK) and Poly-Aryl-Ether-Ketone (PAEK) in sheet form, reinforced with carbon fibres specifically for aerospace application. The emergence of automated layup procedures, notably within the aerospace sector combined with novel fibre-deposition configurations are enabling far greater design freedoms; however, the process of porosity depletion over time, associated morphology and distribution require further study. This inconsistency in the mechanical performance of composite structures results in unreliable and unpredictable performance in service. This is not acceptable for safety critical applications and limits the adoption of composite structures within aircraft applications despite the materials outperforming aluminium alloys in respect of: weight, corrosion resistance, fire retardation and ease of joining. While acknowledging that there may be a number of potential causes for the variation in mechanical performance of composite structures, this study is exclusively concerned with one factor: the degree of porosity present within the composite material during the compression moulding process; subcategorised to porosity morphology and distribution. It is widely accepted that the greater the porosity, the lower the fatigue strength, due to associated damage micro mechanisms. The development and optimisation of metrological approaches that enable non-destructive evaluation of composite structures during and post-process are seen as vital. The dependent variable in this study is defined as in-process porosity measured by volume. It is hypothesized that the degree of in-process porosity during compression moulding is influenced by at least four-parameters: process temperatures, temperature profile, pressure profile and material chemistry. These are the independent variables. Pressure is an important consideration but will be maintained constant in initial phases of the study pending development of effective research methods. Funding is sought to enable research into a process/approach that exploits this advance in technology for metrology purposes. The university is looking for aerospace composite companies that can help build and test aircraft wing structures from PEEK (polyetheretherketone) and/or carbon fibre materials. Expressions of Interest Deadline: 5th June 2020 Call Deadline: 30th June 2020
Type (e.g. company, R&D institution…), field of industry and Role of Partner Sought:
Types: - Advanced Materials, - Aerospace, - Light Weight Composite Materials, - Carbon Fibre and PEEK moulding companies, Role: - Building aircraft wing structures, - Testing, - Recording data and results, - Pressure testing, Also research in to the ongoing novel characterisation of composite manufacturing technique so ideally they would also like to have an industrial partner to have the role as the end user for this data collection.
Technical Specification or Expertise Sought:
Areas of expertise sought would ideally be from aerospace and advanced material companies that can help with: - Research into a process/approach that exploits this advance in technology for metrology purposes. - Pressure testing. - To build PEEK (Polyetheretherketone) structures - aircraft wings. - Building Carbon Fibre structures - aircraft wings. - Collections and gathering of data to show results. And research in to the ongoing novel characterisation of composite manufacturing technique and they would like to have an industrial partner to be an end user for this Data.
Stage of Development:
Comments Regarding Stage of Development:
The research objectives are as follows: 1 - By July 2021, to have established CT Scanning and analysis methods for in-process evaluation on the effects of process temperature, temperature profile and material chemistry on the porosity within a composite structure (measured as a volume cubic millimetres) during compression moulding. 2 - By September 2022, to have defined and recorded the approach/process by which CT scanning and analysis can be used to evaluate the in-process development of porosity of a composite structure during compression moulding. 3 - By September 2023, to have gathered preliminary data relating to the effects of three independent variables: process temperature, temperature profile and material chemistry on the in-process quantification of porosity within a composite structure. The University's current research has taken them to TRL 2 where the principles of in-process evaluation of porosity using CT scanning are demonstrated through experimentation. This feasibility study will move them towards TRL 3 where early proof of concept is demonstrated in the lab.
Comments Regarding IPR Status:
The proposed feasibility study should enable the definition and physical recording of a metrology approach for the in-process evaluation of porosity within a composite structure during compression moulding. This process will be communicated with the scientific community through the publishing of a journal paper and dissemination via conference proceedings. They will also gather preliminary data relating to the effects of four independent variables: process temperatures, temperature profile, pressure profile and material chemistry on the in-process quantification of porosity within a composite structure. This data will be of publishable quality and will likely raise industrial interest from partner organisations such as Airbus (UK) who are investigating the potential for using thermoplastics within wing structures.