TY - JOUR
T1 - Optimal design, manufacturing and testing of non-conventional laminates
AU - Peeters, Daniël M.J.
AU - Irisarri, François Xavier
AU - Groenendijk, Chris
AU - Růžek, Roman
PY - 2019/2/15
Y1 - 2019/2/15
N2 - Composite materials are finding increasing application, for example in commercial aircraft. Traditionally fiber angles are restricted to 0°,±45° and 90°. The current work exploits the possibility of using multiple ’non-conventional’ laminates where either fiber steering (‘variable stiffness’), ply drops (‘variable thickness’), or a combination of both is used. This leads to varying mechanical properties which means the load is being redistributed, increasing the overall buckling load. A flat panel of 400×600 mm loaded in uni-axial compression is optimized in the current work. As a benchmark a conventional laminate is used. The non-conventional laminates are 15% lighter to emphasize the possible weight savings. Only using variable stiffness or variable thickness is experimentally shown to not be sufficient to match the buckling load of the benchmark panel. However, using a combination of both, a 10% increase in the buckling load was found for a panel that is 15% lighter. This highlights the potential of non-conventional laminates.
AB - Composite materials are finding increasing application, for example in commercial aircraft. Traditionally fiber angles are restricted to 0°,±45° and 90°. The current work exploits the possibility of using multiple ’non-conventional’ laminates where either fiber steering (‘variable stiffness’), ply drops (‘variable thickness’), or a combination of both is used. This leads to varying mechanical properties which means the load is being redistributed, increasing the overall buckling load. A flat panel of 400×600 mm loaded in uni-axial compression is optimized in the current work. As a benchmark a conventional laminate is used. The non-conventional laminates are 15% lighter to emphasize the possible weight savings. Only using variable stiffness or variable thickness is experimentally shown to not be sufficient to match the buckling load of the benchmark panel. However, using a combination of both, a 10% increase in the buckling load was found for a panel that is 15% lighter. This highlights the potential of non-conventional laminates.
KW - Fibre placement
KW - Fibre steering
KW - Testing
KW - Variable stiffness
KW - Variable thickness
UR - http://www.scopus.com/inward/record.url?scp=85056735992&partnerID=8YFLogxK
U2 - 10.1016/j.compstruct.2018.10.062
DO - 10.1016/j.compstruct.2018.10.062
M3 - Article
AN - SCOPUS:85056735992
SN - 0263-8223
VL - 210
SP - 29
EP - 40
JO - Composite Structures
JF - Composite Structures
ER -