Emmajane Erskine

1 Introduction Carbon-epoxy laminates are gaining favour in aircraft structures due to their numerous advantages over metallic materials. These benefits include weight reduction, high strength-to-weight ratio, corrosion resistance, and lower manufacturing costs resulting from advancements in production technologies [1]. Consequently, carbon-epoxy is frequently used to manufacture load-bearing laminated components in aircraft structures, such as wing or tail-plane spars [2].

4.4.1 Tensile experiments Figures 9 and 13 show the tensile load–displacement and tensile stress–strain relationship for each CFRP laminate, whilst Figure 10 shows the ultimate tensile strength and tensile failure load as a function of temperature for each CFRP laminate. The data in Figure 9 shows that all CFRP specimens exhibit linear behaviour until they reach peak load and fail, irrespective of fibre orientation.

Material Integrity and fate of particulates released from carbon fibre composites containing nanomaterials during simultaneous fire and impact Robert Chapple, Laurent Ferry, José-Marie Lopez-Cuesta, Carine CHIVAS-JOLY, Emmajane Erskine and Baljinder Kandola Abstract Nanomaterials are usually incorporated in the polymeric resin matrix of the carbon fibre-reinforced composites (CFC) to enhance their mechanical and thermal performances.