Design Space Interrogation for New C-Ply Laminate Architectures

York, C. B. and de Almeida, S. F. M. (2016) Design Space Interrogation for New C-Ply Laminate Architectures. In: ECCM 17: 17th European Conference on Composite Materials, Munich, Germany, 26-30 June 2016,

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Spread tow Non-Crimp Fabric (NCF) materials, e.g. C-PlyTM , are now available in a range of areal weights and ply architectures, including 0/45, 0/-45, 45/-45 and 0/90, which correspond to the standard ply orientations employed in traditional UD material lay-ups. The benefit of NCF material is generally associated with increased deposition rate, but this advantage may be offset by reduced design freedoms when a specific form of mechanical coupling behaviour is required, ply terminations must also be introduced and thermal warping distortion eliminated. This article investigates the extent to which new NCF architectures, based on 0/45, 0/-45, 45/-45 and 0/90 NCF can be tailored to achieve warp free tapered laminates without the need for deposition with off axis alignment, and thus avoid ply discontinuities. Interrogation of the available lamination parameter design space is used to demonstrate the effect of applying ply termination constraints. Finally, buckling factor contours are mapped onto the lamination parameter design space to assess the bounds, under compression and shear loading, for infinitely long simply supported plates.

Item Type:Conference Proceedings
Glasgow Author(s) Enlighten ID:York, Dr Christopher
Authors: York, C. B., and de Almeida, S. F. M.
College/School:College of Science and Engineering > School of Engineering > Aerospace Sciences
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Project CodeAward NoProject NamePrincipal InvestigatorFunder's NameFunder RefLead Dept
724671The Flexible Wing Project: Advanced Tailoring Strategies for Laminated Composite MaterialsChristopher YorkThe Royal Academy of Engineering (RAE)NRCP1516/4/50ENG - AEROSPACE SCIENCES