On Influence of Kinematics to Equivalent Linear Damping of Helicopter Blade Hydraulic Damper

HU Guo-cai; XIANG Jin-wu; ZHANG Xiao-gu

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Article Navigation > Applied Mathematics and Mechanics > 2002 > 23(8): 819-826

HU Guo-cai, XIANG Jin-wu, ZHANG Xiao-gu. On Influence of Kinematics to Equivalent Linear Damping of Helicopter Blade Hydraulic Damper[J]. Applied Mathematics and Mechanics, 2002, 23(8): 819-826.

Citation:

HU Guo-cai, XIANG Jin-wu, ZHANG Xiao-gu. On Influence of Kinematics to Equivalent Linear Damping of Helicopter Blade Hydraulic Damper[J]. Applied Mathematics and Mechanics, 2002, 23(8): 819-826.

Citation:

HU Guo-cai, XIANG Jin-wu, ZHANG Xiao-gu. On Influence of Kinematics to Equivalent Linear Damping of Helicopter Blade Hydraulic Damper[J]. Applied Mathematics and Mechanics, 2002, 23(8): 819-826.

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On Influence of Kinematics to Equivalent Linear Damping of Helicopter Blade Hydraulic Damper

Institute of Aircraft Design and Research, Beijing University of Aeronautics and Astronautics, Beijing 100083, P.R.China

Received Date: 2000-09-25
Rev Recd Date: 2002-03-26
Publish Date: 2002-08-15

Abstract

Abstract

An analytical model of hydraulic damper was presented in forward flight accounting for pitch/flap/lag kinematic coupling and its nonlinear force-velocity curve.The fourth order Runge-Kutta was applied to calculate the damper axial velocity in time domain.Fourier series based moving block analysis was applied to calculate equivalent linear damping in terms of transient responses of damper axial velocity.Results indicate that equivalent linear damping will be significantly reduced if pitch/flap/lag kinematic coupling introduced for notional model and flight conditions.
- nonlinear damping,
- hydraulic damper,
- equivalent linear damping,
- helicopter rotor blade,
- kinematic coupling

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References(8)

References

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