OS1411 熱変形を考慮した複合材料補強パネルの積層構成最適化に関する基礎的研究(OS14-3 複合材料・導電材料の弾性数理解析,OS-14 弾性数理解析の発展と新展開1)

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This paper discusses optimum design of a stiffened composite panel: the panel is widely used for weight reduction in aerospace structures. Anisotropic thermal expansion coefficients of the composite laminates causes complicated deformation of the panel after the curing.. In previous researches of the stacking sequence optimizations, the optimizations were performed without considering thermal deformation: a response surface was used to obtain an objective function at low computational cost, and lamination parameters were sued as variables for the response surface of the objective function such as buckling load ratio. However, the thermal deformation caused by the temperature change after curing must be considered as a constraint factor for actual composite structures. In the present study, therefore, thermal deformation is dealt with as a constraint for a stacking sequence optimization problem. Three surrogate models of the thermal deformation are discussed here: a conventional method using lamination parameters; a new method using lamination parameters and thermal coefficients; a modified new method As a result, the modified new method is shown to be effective for the surrogate model.
2011-07-16