On tapered warp-free laminates with single-ply terminations

York, Christopher

doi:10.1016/j.compositesa.2015.01.022

Cited by 17 publications

(14 citation statements)

References 13 publications

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“…When A 16 , A 26 0, in-plane shear with extension coupling exists, and in the case when D 16 , D 26 0 out-of-plane bending and twisting coupling appears. According to the international literature (e.g., [1][2][3][4]40]), the used notations for the ABD laminate stiffness matrix are presented in Table 3. In the parametric study, the layer arrangements were assumed in such a way as to check all possible cases of coupling matrix B presented in Table 3.…”

Section: Layer Arrangements With Their Abd Laminate Stiffness Matrixmentioning

confidence: 99%

“…York analyzed the HTCS design of laminates with non-standard ply angle orientation (+60 • , −60 • , 0 • and 90 • ) [1]. Furthermore, he analyzed new design methods for tapered laminates under various types of load [2]. Shamsudin and York [3] provide in-depth analyses of standard laminate stacking sequences in order to obtain thermally immune structures.…”

Section: Introductionmentioning

confidence: 99%

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The Influence of the Layer Arrangement on the Distortional Post-Buckling Behavior of Open Section Beams

2020

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The paper deals with the design of the stacking sequence of layers in the laminate beams with open-cross sections in order to create the desired behavior in the post-buckling range. Laminate beams with channel and lipped channel cross-sections made of glass fiber reinforced polymer (GFRP) laminate with different layer arrangements (symmetrical and nonsymmetrical) have been considered. In case of the nonsymmetrical stacking sequences, hygro-thermally curvature stable (HTCS) laminates have been taken into account. Pure bending was assumed as the type of load. In the case of beams with open cross-sections, this load type can cause the lateral-distortional buckling mode. A parametric study was performed to analyze the influence of layer arrangement on post-buckling behavior. The finite element method was used to developed numerical models and conduct simulations. Additionally, the experimental tests of the channel section beams were performed in order to validate the developed numerical models.

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Section: Layer Arrangements With Their Abd Laminate Stiffness Matrixmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

The Influence of the Layer Arrangement on the Distortional Post-Buckling Behavior of Open Section Beams

2020

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“…Based on the understanding of stress distribution near ply drops, a number of stress based and energy-release-rate (ERR) based approaches have been proposed to predict delamination onset and growth [1,7,11,12]. Useful optimisation methods of designing a tapered laminates were also presented based on a generic algorithm or stacking sequence tables [13][14][15].…”

Section: Introductionmentioning

confidence: 99%

An experimental and numerical investigation into damage mechanisms in tapered laminates under tensile loading

Zhang

Kawashita

Jones

et al. 2020

Composites Part A: Applied Science and Manufacturing

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“…However, thermal warping distortions are eliminated only when the number of repeats (r) remain large.Recent research has however demonstrated that tailored Non-Crimp Fabric (NCF) designs, based on 0/45 and 0/-45 architectures, can produce fully uncoupled laminates or laminates with Extension-Shearing and/or Bending-Twisting coupling, and that all have immunity to thermal warping distortion [7]. The extent to which tapered laminate designs can be achieved, without introducing unwanted thermo-mechanical coupling, was also investigated through a layer termination algorithm to introduce single-layer [8] or, where necessary, multiple-layer terminations [4,7]. This research followed related studies on laminate design for uni-directional (UD) fibre architectures for fully uncoupled laminates [9], and those with Extension-Shearing [10] and/or Bending-Twisting coupling [11,12].The results presented in this article investigate these four laminate classes constructed from the new NCF architectures, see Fig.…”

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confidence: 99%

“…Extension-Shearing or E-S coupled, and Extension-Shearing and Bending-Twisting or E-S;B-T coupled warp-free laminate classes are reported inTable 1. Each row corresponds to a particular layer number grouping, nNCF, with NCF layers and the equivalent ply number grouping, nUD, with UD layers are given in parentheses, which correspond to previously derived results[8] with matching ply contiguity (≤ 2) constraint. This ply contiguity is a natural constraint, arising from the NCF architecture, which accounts for the reduced design space.…”

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confidence: 99%

Tapered laminate designs for new non-crimp fabric architectures

York

Almeida

2017

Composites Part A: Applied Science and Manufacturing

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Non-Crimp Fabric (NCF) materials are now available in a range of areal weights and layer 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, layer terminations must be introduced and/or thermal warping distortion eliminated.This article investigates the extent to which new NCF architectures can be tailored to achieve warp free tapered laminates with mechanical Extension-Shearing Bending-Twisting couplings, by single axis (longitudinal) deposition of all ply angles; thus avoiding ply discontinuities that may be introduce in large component manufacture.Lamination parameter design spaces are used to demonstrate the extent of the feasible solutions both before and after applying a laminate tapering scheme. 2 IntroductionDesign issues associated with tapered composite laminates have been comprehensively reviewed in a number of articles [1,2]. These reviews reveal an extensive literature, focussing primarily on delamination initiation and propagation in the region of ply terminations, but also reveal that little attention has been given to the extent to which plies may be dropped without introducing thermal warping distortion and associated changes in mechanical coupling characteristics. Indeed, current tapering schemes tend to consider only short ramps or pad-ups, and few [3] consider thermal warping and the associated locked in stresses. By contrast, tapering schemes for continuous wing or fuselage panel construction, in which only single ply terminations may be necessary between adjacent ribs or ring stiffeners, to satisfy strength and/or buckling constraints, are currently restricted to balanced and symmetric laminate designs. Hence, with few exceptions [4], such designs generally require a minimum of 4 ply terminations to avoid introducing thermal warping distortions; their inherent mechanical Bending-Twisting coupling characteristics can also lead to significant reductions in the compression buckling strength [5]. New joint requirements for aero-elastic tailoring and more efficient manufacturing of composite wing or winglet construction requires a more considered tapering scheme, which has resulted in the recent development of bi-angle non-crimp fabrics (NCF) architectures, consisting of two plies of UD material, one at 0° and the other at either a shallow angle,   20°, or the standard 45° angle, stitched together. The repeating biangle [/0]rT NCF concept [6] has the potential to reduce wet lay-up times by half, in comparison to traditional UD tape. In what follows, a layer (of NCF material) contains 2 plies (of UD material). Ply terminations can also be applied to any layer without 3 changing the Extension-Shearing and Bending-Twisting dominant mechanical coupling, necessary for aero-elastic tailoring of wi...

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On tapered warp-free laminates with single-ply terminations

Cited by 17 publications

References 13 publications

The Influence of the Layer Arrangement on the Distortional Post-Buckling Behavior of Open Section Beams

The Influence of the Layer Arrangement on the Distortional Post-Buckling Behavior of Open Section Beams

An experimental and numerical investigation into damage mechanisms in tapered laminates under tensile loading

Tapered laminate designs for new non-crimp fabric architectures

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