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- W2023876546 abstract "Optimization studies are carried out for a four-bladed, soft in-plane hingeless rotor consisting of a twocell composite box-beam spar. The design variables are the ply angles of the box-beam walls. The objective functions are the vibratory hub loads and the vibratory blade bending moments; constraints are imposed on blade rotating frequencies and aeroelastic stability. The objective functions are first minimized individually, and then a combined optimization is performed to minimize both the objectives simultaneously. As compared to the starting design, the optimum solution results in a 15-60% reduction of the 4/rev hub loads as well as a reduction in the peak-to-peak flap and lag bending moments of 11 and 14%, respectively. Starting from an initially infeasible starting design with a 3% requirement on lag mode damping, the optimum solution with composite chordwise bending-torsion coupling results in an increase in lag mode damping of over 200% compared to the starting design." @default.
- W2023876546 created "2016-06-24" @default.
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- W2023876546 date "1996-07-01" @default.
- W2023876546 modified "2023-09-26" @default.
- W2023876546 title "Aeroelastic optimization of a helicopter rotor to reduce vibration and dynamic stresses" @default.
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- W2023876546 doi "https://doi.org/10.2514/3.47018" @default.
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