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- W2091004354 abstract "A coupled rotor-fuselage vibration analysis is formulated to analyze the effect of rotor system faults on fuselage vibrations and rotor-blade displacements in both hover and forward-flight conditions. Two groups of rotor-system faults, adjustable and nonadjustable component faults, are modeled. Results are presented for an SH-60 helicopter and are compared with available flight-test data. A detailed aeroelastic analysis is carried out where each rotor blade is modeled individually such that rotor dissimilarity can be considered. A fuselage NASTRAN model is incorporated and coupled with the rotor model analysis. The centrifugally tuned, hub-mounted bifilar vibration absorbers are also modeled, and the coupled rotor-fuselage-bifilar nonlinear equations are solved using finite element method in space and time" @default.
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- W2091004354 date "2004-03-01" @default.
- W2091004354 modified "2023-09-23" @default.
- W2091004354 title "Vibration Prediction for Rotor System with Faults Using Coupled Rotor-Fuselage Model" @default.
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- W2091004354 doi "https://doi.org/10.2514/1.9330" @default.
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