The key parameters of the in-situ consolidation of carbon fibre reinforced poly-ether-etherketone (AS4-CF/PEEK) by automated tape placement (ATP) process were investigated by manufacturing of continuous rings and by laying tape onto pre-consolidated laminates. In order to establish and understand correlations between the process parameters and mechanical properties, a number of parametric studies were performed by manufacturing and testing the interlaminar shear strength, single lap shear strength and fracture toughness samples. The main process parameters investigated were the compaction force, tape laying speed and tool temperature. To achieve a uniform heat distribution across the thermoplastic tape, a new nozzle was designed. Baseline samples were also manufactured using the autoclave process to provide a comparison for the ATP composites produced. Optical microscopy was used for investigating the microstructure of composites compared.

Abstract.A cradle-to-grave life cycle assessment (LCA) of structural aircraft materials has been utilised to assess and compare the total emissions produced during manufacturing, use and disposal of aerospace materials and their selected components. First, a comparison of aluminium, GLARE and carbon fibre reinforced polymer (CFRP) plates was performed to investigate the potential of lightweight composites in reducing aviation emissions. Subsequently, a case study is presented on a tubular component for which more accurate manufacturing data were directly available. A structural steel tube was replaced with a composite tubular component. The analysis has shown that once the composite material is used as a component in the aircraft, there is a cumulative saving of aircraft fuel and emissions, in particular from CFRP structures. The environmental analysis included the long-term use predictions for CFRPs, involving detailed raw materials production, use and operation, and disposal scenarios.

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This paper investigates the effect of the fabric architecture and the z-binding yarns on the compression after multiple impacts behavior of composites. Four fiber architectures are investigated: non-crimp fabric (NCF), 2D plain weave (2D-PW), 3D orthogonal plain (ORT-PW) and twill (ORT-TW) weave. The specimens were subjected to single and multiple low-velocity impacts at different locations with the same energy level (15 J). Non-destructive techniques including ultrasonic C-scanning, X-ray CT and Digital Image Correlation (DIC) are employed to quantitatively analyze and capture the Barely Visible Impact Damage (BVID) induced in the specimens. Although the absorbed energy was approximately the same, damage was the least in 3D woven architectures. In the case of compression after impact, 3D woven composites demonstrated a progressive damage behavior with the highest residual strength (~92%) while 2D plain weave and NCF specimens showed suddenly catastrophic damage and the residual strength of~65% and~55% respectively.