TY - GEN
T1 - Initial sizing optimisation of anisotropic composite panels with T-shape stiffeners
AU - Herencia, J. Enrique
AU - Weaver, Paul M.
AU - Friswell, Michael I.
PY - 2007
Y1 - 2007
N2 - This paper provides an approach to perform initial sizing optimisation of anisotropic composite panels with T-shape stiffeners. The method divides the optimisation problem into two levels. At the first level, composite optimisation is performed using Mathematical Programming (MP), where the skin and the stiffeners are modelled using lamination parameters accounting for their 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 stiffened panel is subjected to a combined loading under strength, buckling and practical design constraints. Buckling constraints are computed using Closed Form (CF) solutions and energy methods (Rayleigh-Ritz). Conservatism is partially removed in the buckling analysis considering the skin-stiffener flange interaction and decreasing the effective width of the skin. Furthermore, the design and manufacture of the stiffener is embedded within the design variables. At the second level, the actual skin and stiffener lay-ups are obtained using Genetic Algorithms (GAs), accounting for manufacturability and design practices. This two level approach permits the separation of the analysis (strength, buckling, etc), which is performed at the first level, from the laminate stacking sequence combinatorial problem, which is dealt efficiently with GAs at the second level.
AB - This paper provides an approach to perform initial sizing optimisation of anisotropic composite panels with T-shape stiffeners. The method divides the optimisation problem into two levels. At the first level, composite optimisation is performed using Mathematical Programming (MP), where the skin and the stiffeners are modelled using lamination parameters accounting for their 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 stiffened panel is subjected to a combined loading under strength, buckling and practical design constraints. Buckling constraints are computed using Closed Form (CF) solutions and energy methods (Rayleigh-Ritz). Conservatism is partially removed in the buckling analysis considering the skin-stiffener flange interaction and decreasing the effective width of the skin. Furthermore, the design and manufacture of the stiffener is embedded within the design variables. At the second level, the actual skin and stiffener lay-ups are obtained using Genetic Algorithms (GAs), accounting for manufacturability and design practices. This two level approach permits the separation of the analysis (strength, buckling, etc), which is performed at the first level, from the laminate stacking sequence combinatorial problem, which is dealt efficiently with GAs at the second level.
UR - http://www.scopus.com/inward/record.url?scp=84870541615&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:84870541615
SN - 9781604239737
T3 - Society of Allied Weight Engineers - 66th Annual International Conference on Mass Properties Engineering 2007
SP - 31
EP - 61
BT - Society of Allied Weight Engineers - 66th Annual International Conference on Mass Properties Engineering 2007
T2 - 66th Annual International Conference on Mass Properties Engineering 2007
Y2 - 26 May 2007 through 31 May 2007
ER -