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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

Lee,  A. C., Kang,  Y., Tsai,  K. L., and Hsiao,  K. M., 1992, “Transient Analysis of an Asymmetric Rotor-Bearing System during Acceleration,” ASME J. Ind., 114(4), pp. 465–475.
Ganesan, R., and Sankar, T. S., 1993, “Resonant Oscillations and Stability of Asymmetric Rotors,” Proc. of the 14th Biennial ASME Conference on Mechanical Vibration and Noise, ASME DE, 56 , pp. 19–22.
Spence,  A. M., and Cele,  R., 1995, “Coupled Rotor Fuselage Dynamics and Aero-Elasticity in Turning Flight,” J. Am. Helicopter Soc., 40(1), pp. 47–58.
Cao,  Y., 1999, “Modelling the Unsteady Aerodynamic Forces of a Maneuvering Rotor,” Aircraft Engineering and Aerospace Technol., 71(5), pp. 444–450.
Bagai,  A., Leishman,  J. G., and Park,  J., 1999, “Aerodynamic Analysis of a Helicopter in Steady Maneuvering Flight Using a Free-Vortex Rotor Wake Model,” J. Am. Helicopter Soc., 44(2), pp. 109–120.
Park, J. S., and Leishman, J. G., 1999, “Investigation of Unsteady Aerodynamics on Rotor Wake Effects in Maneuvering Flight,” Annual Forum Proceedings-American Helicopter Society, 1 , pp. 467–480.
Krothapalli,  K. R., Prasad,  J. V. R., and Peters,  D. A., 2001, “Helicopter Rotor Dynamic Inflow Modelling for Maneuvering Flight,” J. Am. Helicopter Soc., 46(2), pp. 129–139.

Figures

Grahic Jump Location
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)
Grahic Jump Location
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
Grahic Jump Location
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)
Grahic Jump Location
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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