Abstract
Continuous curvilinear variable stiffness (CCVS) is presented as a novel solution to improve the load carrying capacity of a fuselage panel with a cutout. The CCVS technique allows for the tow paths to curve around cutouts of arbitrary geometry with initial fiber angle and geometry as design inputs. An optimum CCVS design is generated using a genetic algorithm method coupled with a finite element model in NASTRAN and the results are compared with those obtained using a quasi-isotropic laminate. The optimized CCVS laminate is found to improve the load carrying capacity compared with the quasi-isotropic design by 57%.
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