Laminate Design with Non-Standard Ply Angles for Optimised In-Plane Performance

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Citation (Scopus)

Abstract

New structural efficiency diagrams are presented for laminates, showing that additional mass is incurred when (i) laminate balancing axes are not aligned with principal loading axes and (ii) principal loading ratios vary within a part with fixed ply percentages. This presents an opportunity for fibre steering and laminate tailoring in aerospace design. Non-standard ply angles are shown to offer small mass savings when laminate balancing axes are not aligned with principal loading axes. However, such angles may enhance performance in other aspects (e.g. damage tolerance, ease of manufacture, buckling resistance) whilst matching the in-plane stiffness of standard ply angle designs.
Original languageEnglish
Title of host publication21st International Conference for Composite Materials
Place of PublicationXi'an
Number of pages12
Publication statusPublished - Aug 2017

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Laminates
Damage tolerance
Buckling
Stiffness
Fibers

Cite this

Laminate Design with Non-Standard Ply Angles for Optimised In-Plane Performance. / Nielsen, Mark; Johnson, Kevin; Rhead, Andrew; Butler, Richard.

21st International Conference for Composite Materials. Xi'an, 2017. 3815.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Nielsen M, Johnson K, Rhead A, Butler R. Laminate Design with Non-Standard Ply Angles for Optimised In-Plane Performance. In 21st International Conference for Composite Materials. Xi'an. 2017. 3815
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N2 - New structural efficiency diagrams are presented for laminates, showing that additional mass is incurred when (i) laminate balancing axes are not aligned with principal loading axes and (ii) principal loading ratios vary within a part with fixed ply percentages. This presents an opportunity for fibre steering and laminate tailoring in aerospace design. Non-standard ply angles are shown to offer small mass savings when laminate balancing axes are not aligned with principal loading axes. However, such angles may enhance performance in other aspects (e.g. damage tolerance, ease of manufacture, buckling resistance) whilst matching the in-plane stiffness of standard ply angle designs.

AB - New structural efficiency diagrams are presented for laminates, showing that additional mass is incurred when (i) laminate balancing axes are not aligned with principal loading axes and (ii) principal loading ratios vary within a part with fixed ply percentages. This presents an opportunity for fibre steering and laminate tailoring in aerospace design. Non-standard ply angles are shown to offer small mass savings when laminate balancing axes are not aligned with principal loading axes. However, such angles may enhance performance in other aspects (e.g. damage tolerance, ease of manufacture, buckling resistance) whilst matching the in-plane stiffness of standard ply angle designs.

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