The intermixing of the thermoplastic matrix fiber and the reinforcing carbon fiber gives a preform that can be easily fabricated into laminates with low void content. This was demonstrated with the intermixing of Celion 3000 with a Celanese liquid crystal polymer fiber, polybutylene terepthalate fiber, or polyetheretherketone fiber. The objectives were attained with the development of the hybrid yarn concept whereby, thermoplastic fiber can be intimately intermixed with carbon fiber into a hybrid yarn. The Y spars were fabricated using AS4 (6K)/PEEK 150g commingled angle interlock 0/90-degree woven preforms with +45-degree commingled plies stitched using high strength Toray carbon thread and processed by autoclave consolidation.Įfforts were directed to develop processing methods to make carbon fiber/ thermoplastic fiber preforms that are easy to handle and drapeable, and to consolidate them into low void content laminates. The fabrication of representative Y spars by consolidation methods will be described. The focus has been on minimizing part count (mechanical fasteners, clips, number of stiffeners, etc.), by using cost effective textile reinforcement concepts that provide improved damage tolerance and out-of-plane load capability, low-cost resin transfer molding processing, and thermoplastic forming concepts. In this on-going effort, design trade studies were conducted to arrive at advanced wing designs that integrate new material forms with innovative structural concepts and cost effective fabrication methods. The Novel Composites for Wing and Fuselage Applications (NCWFA) program has as its objective the integration of innovative design concepts with cost effective fabrication processes to develop damage-tolerant structures that can perform at a design ultimate strain level of 6000 micro-inch/inch. Processes that have been identified as meeting these goals are textile preforms that use resin transfer molding (RTM) and consolidation forming. The use of innovative cost effective material forms and processes is being considered for fabrication of future primary aircraft structures. PMID:28772977Ĭonsolidation of graphite thermoplastic textile preforms for primary aircraft structure The TPU composite strength was mainly dependent upon constituent fibre stress-strain behaviour and fibre segment orientation distribution. In summary, increasing the strength and degree of consolidation of nonwoven preforms did not translate to an increase in the strength of resulting fibre reinforced TPU- composites. The linear density of fibres and the punch density, a key process variable used to consolidate the nonwoven preform, were varied to study the influence on resulting FRP mechanical properties. Reinforcement with standard fibres manifold improved the tensile modulus and strength of the reinforced composites and the relationship between fibre, fabric and composite’s mechanical properties was studied. Nonwoven preform fibre compositions were selected from lyocell, polyethylene terephthalate (PET), polyamide (PA) as well as para-aramid fibres (polyphenylene terephthalamide PPTA). The mechanical behaviour of FRPs based on mechanically bonded nonwoven preforms composed of either low or high modulus fibres in a thermoplastic polyurethane (TPU) matrix were compared following compression moulding. Reinforcement of flexible fibre reinforced plastic (FRP) composites with standard textile fibres is a potential low cost solution to less critical loading applications. Tausif, Muhammad Pliakas, Achilles O’Haire, Tom Goswami, Parikshit Russell, Stephen J. Mechanical Properties of Nonwoven Reinforced Thermoplastic Polyurethane Composites The mechanical performance is shown to surpass that of 40 wt.% GMT and has properties equivalent to those of 40 wt.% GMTex at both 20Â☌ and 80Â☌. A viable processing route is proposed with typical cycle times below 40 s (for a plate 0.5 Ã- 0.5 m2, weighing 2 kg), enabling high production capacity from one line. The process stages are examined to optimize part quality and throughput versus processing parameters. The preforms are then preheated and press formed to obtain the final part. The as-placed fibres are heat-set for improved handling before an optional preconsolidation stage. The thermoplastic programmable powdered preforming process (TP-P4) uses commingled glass and polypropylene yarns, which are cut to length before air assisted deposition onto a vacuum screen, enabling local preform areal weight tailoring. E.Ī novel thermoplastic composite preforming and moulding process is investigated to target cost issues in textile composite processing associated with trim waste, and the limited mechanical properties of current bulk flow-moulding composites. Rapid Processing of Net-Shape Thermoplastic Planar-Random Composite Preforms
0 Comments
Leave a Reply. |