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- W2353289963 abstract "Aeroelastic model is developed to analyze aeroelastic stability of helicopter rotor blade with swept tips. Parameters of blade pre cone, pre twist and tip sweep angle are considered in model involving nonlinear effects. Nonlinear transformation relations are specially derived for swept tip of blade. The partial differential equations of motion are discretized by finite element in space using Hamilton's principle. Influence study of tip angle on aeroelastic stability of helicopter rotor is implemented by developing computer codes. Validation studies are first carried out for ITR rotor with straight tip in hover to correlate the calculated results with experimental data. Secondly aeroelastic stability correlation studies are implemented on Bo 105 rotor with swept tip in forward flight to correlate the calculated results by developed codes with the results of UMARC. Numerical results show that the influence of tip sweep angle on aeroelastic stability is considerable in hover and forward flight. The first lag mode damping of blade decreases with tip sweep angle. Nonlinear transformation relations are very important for aeroelastic stability analysis of rotor blade with swept tip, especially in case of large sweep angle." @default.
- W2353289963 created "2016-06-24" @default.
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- W2353289963 date "2003-01-01" @default.
- W2353289963 modified "2023-09-25" @default.
- W2353289963 title "Aeroelastic Stability Analysis of Helicopter Rotor Blade with Swept Tips" @default.
- W2353289963 hasPublicationYear "2003" @default.
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