| Titre : |
Non-destructive characterisation of composite microstructures |
| Type de document : |
texte imprimé |
| Auteurs : |
Robert A. Smith, Auteur ; Ningbo Xie, Auteur ; Stephen R. Hallett, Auteur |
| Année de publication : |
2016 |
| Article en page(s) : |
p. 59-61 |
| Note générale : |
Bibliogr. |
| Langues : |
Anglais (eng) |
| Catégories : |
Composites -- Analyse
Contrôle non destructif
Microstructures -- Analyse
Simulation par ordinateur
|
| Index. décimale : |
620.11 Matériaux (propriétés, résistance) |
| Résumé : |
The UK's non-destructive testing community is developing game-changing composite inspecting technology to meet environmental challenges. Mapping of the microstructure could ensure conformance to design while enabling affordable and rapid manufacture. |
| Note de contenu : |
- Fig. 1. Wedge specimen containing ply drops, made from 0.189 mm plies and incorporating 0.04 mm resin layers. a) Ultrasound-derived front-surface (red), back-surface (red) and resin-layer (green) locations ; b) X-ray CT slice ; c) ultrasount overlaid on X-ray CT. The ultrasound scan was performed with a 38 mm focal length spherical-focus probe with a 7.5 MHz nominal peak frequency
- Fig. 2. Out-of-plane angular analysis of a 100 mm long section of a tapered carbon-fibre composite laminate - the same specimen and scan data as in figure 1. The colour represent the ply angle and the brightness is the superimposed instantaneous phase from which the ply angles were calculated
- Fig. 3. Vector field data for the unit vector field parallel to the fibres with fibre-tow 'tubes" illustrating the wrinkling and in-plane waviness in each ply of a specimen with layup : [45,0, -45, 90, -45, 0, 45], showing (a) 90°, (b) 45° and (d) - 45° plies. Note the aspect ration used exaggerates out-of-plane distances with 10x magnification (image from reference[3])
- Fig. 4. Model generated for specimen from Fig. 3 with a tensile strain applied in the x direction. Colour shows U3 displacement in the laminate thickness direction. Red colours represent a positive displacement and blue represents a negative displacement
- Fig. 5. Damage distributionof a 12° coupon : (a) photograph of initial coupon failure, (b) delamination prediction (colours), (c) matrix-cracking and fibre-kinking failure prediction (colours)
- Fig. 6. Relationship between failure stress knock-down (colour scale in %) and maximum angle (vertical axis), as a function of the wrinkle amplitude and wavelength. Black 'x' locations represent the modelled values before interpolation. The extent of the wrinkled zone was kept the same throughout |
| En ligne : |
https://drive.google.com/file/d/1dpw4rmQAgKR56kzzwZWjCX0Xmh69cTjy/view?usp=drive [...] |
| Format de la ressource électronique : |
Pdf |
| Permalink : |
https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=28180 |
in JEC COMPOSITES MAGAZINE > N° 109 (11-12/2016) . - p. 59-61
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