TY - GEN
T1 - Laminate Design with Non-Standard Ply Angles for Optimised In-Plane Performance
AU - Nielsen, Mark
AU - Johnson, Kevin
AU - Rhead, Andrew
AU - Butler, Richard
PY - 2017/8
Y1 - 2017/8
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.
UR - http://www.iccm-central.org/Proceedings/ICCM21proceedings/papers/3815.pdf
UR - https://www.scopus.com/pages/publications/85053162227
M3 - Chapter in a published conference proceeding
BT - 21st International Conference for Composite Materials
CY - Xi'an
ER -