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TECHNICAL PAPERS

Study on the Dynamics of a Rotor in a Maneuvering Aircraft

[+] Author and Article Information
Fusheng Lin, Guang Meng

State Key Lab of Vibration, Shock & Noise, Shanghai Jiao Tong University, Shanghai 200030, P. R. C.

J. Vib. Acoust 125(3), 324-327 (Jun 18, 2003) (4 pages) doi:10.1115/1.1576422 History: Received August 01, 2002; Revised March 01, 2003; Online June 18, 2003
Copyright © 2003 by ASME
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References

Figures

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Sketch of the rotor system located in an aircraft and the space-fixed stationary coordinates
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The reference frame O1ξηζ and parallel frame O3ξ1η1ζ1
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Influence of accelerating abruptly in vertical direction (constant horizontal velocity component) (U=1, Ge=1, Ω=0.8, zd=0, zd=zd0=100, xd0=100)
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Rotor responses when the aircraft flies in a sine curve (Ω=0.8, U=0.5, Ge=0.5, zd=0, λ=0.00002) (a) Influence of Γ (zd=100) (b) Influence of zd(Γ=50000)
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Influence of the aircraft acceleration in horizontal and vertical directions on rotor accelerating response (Ω0=0.8, xd=0, 10, 50, xd=zd=100, Ge=1, U=1.0) (a) zd0=zd=0 (b) zd0=zd=100
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Rotor accelerating response when the aircraft flies in a sine curve (Ω0=0.8, U=0.5, Ge=1.5, zd=0) (a) Influence of Γ (zd=100, λ=0.00002) (b) Influence of zd(Γ=100, λzd=0.002)
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Rotor accelerating response when the aircraft flies in a sine curve (Ω0=0.3)(U=0.5, Ge=1.5, zd=100, zd=0, λ=0.00002, Γ=0, 50000, 100000)

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