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- W2146128776 abstract "This study aims to determine optimal locations of dual trailing-edge flaps and blade stiffness to achieve minimum hub vibration levels in a helicopter, with low penalty in terms of required trailing-edge flap control power. An aeroelastic analysis based on finite elements in space and time is used in conjunction with an optimal control algorithmtodeterminethe flaptimehistoryforvibrationminimization.Usingtheaeroelasticanalysis,itisfoundthat the objective functions are highly nonlinear and polynomial response surface approximations cannot describe the objectives adequately. A neural network is then used for approximating the objective functions for optimization. Pareto-optimal points minimizing both helicopter vibration and flap power are obtained using the response surface and neural network metamodels. The two metamodels give useful improved designs resulting in about 27% reduction in hub vibration and about 45% reduction in flap power. However, the design obtained using response surface is less sensitive to small perturbations in the design variables." @default.
- W2146128776 created "2016-06-24" @default.
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- W2146128776 date "2011-03-01" @default.
- W2146128776 modified "2023-10-18" @default.
- W2146128776 title "Optimization of Helicopter Rotor Using Polynomial and Neural Network Metamodels" @default.
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- W2146128776 doi "https://doi.org/10.2514/1.c031156" @default.
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