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- W1987807357 abstract "Based on the engineering reality, a calculation model of the rotor unsteady aerodynamics of a small coaxial helicopter in hovering state had been set up. An airfoil unsteady aerodynamic model was established by introducing a set of Leishman-Beddoes semi-empirical indicial response formulas; the aerodynamic interaction between upper and lower rotors of the coaxial helicopter was set up by bringing an interferential factor in the dynamic inflow model, and the Runge-Kutta method was used to obtain the numerical solution of the rigid flapping angle. According to the calculation and analysis, the thrust and torque responses to a rapid collective pitch increase in hovering state were obtained, and the direction response's differences between the semi-differential and full-differential direction control modes were compared." @default.
- W1987807357 created "2016-06-24" @default.
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- W1987807357 date "2010-06-01" @default.
- W1987807357 modified "2023-09-25" @default.
- W1987807357 title "Rotor unsteady aerodynamics research of a small-scale coaxial helicopter in hovering state" @default.
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- W1987807357 doi "https://doi.org/10.1109/iccda.2010.5541284" @default.
- W1987807357 hasPublicationYear "2010" @default.
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