TY - GEN
T1 - Local optimisation of long anisotropic laminated fibre composite panels with T shape stiffeners
AU - Herencia, J. Enrique
AU - Weaver, Paul M.
AU - Friswell, Mike I.
PY - 2006
Y1 - 2006
N2 - A method to locally optimise long anisotropic laminated fibre composite panels with T shape stiffeners is presented. The technique splits the optimisation problem into two levels. At the first level, composite optimisation is performed using mathematical programming (MP), and the skin and stiffeners are modelled using lamination parameters that account for their membrane and flexural anisotropy. Skin and stiffener laminates are assumed to be symmetric, or mid-plane symmetric laminates, with 0, 90, 45, or -45 degree, ply angles. The skin-stiffener configuration is further idealised as a group of flat plate laminates that are rigidly connected. The panel is subjected to a combined case of loading under strength, budding and manufacturing constraints. At the second level, the actual skin and stiffener lay-ups are obtained using a genetic algorithm (GA) and considering the ease of manufacture. This approach offers the advantage of introducing accurate analysis methods such as finite elements at the first level, without significant increases in processing time. Furthermore modelling the laminate anisotropy enables the designer to explore and potentially use elastic tailoring in a beneficial manner.
AB - A method to locally optimise long anisotropic laminated fibre composite panels with T shape stiffeners is presented. The technique splits the optimisation problem into two levels. At the first level, composite optimisation is performed using mathematical programming (MP), and the skin and stiffeners are modelled using lamination parameters that account for their membrane and flexural anisotropy. Skin and stiffener laminates are assumed to be symmetric, or mid-plane symmetric laminates, with 0, 90, 45, or -45 degree, ply angles. The skin-stiffener configuration is further idealised as a group of flat plate laminates that are rigidly connected. The panel is subjected to a combined case of loading under strength, budding and manufacturing constraints. At the second level, the actual skin and stiffener lay-ups are obtained using a genetic algorithm (GA) and considering the ease of manufacture. This approach offers the advantage of introducing accurate analysis methods such as finite elements at the first level, without significant increases in processing time. Furthermore modelling the laminate anisotropy enables the designer to explore and potentially use elastic tailoring in a beneficial manner.
UR - http://www.scopus.com/inward/record.url?scp=34247176728&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:34247176728
SN - 1563478080
SN - 9781563478086
T3 - Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
SP - 6869
EP - 6893
BT - Collection of Technical Papers - 47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
T2 - 47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Y2 - 1 May 2006 through 4 May 2006
ER -