ON INFLUENCE OF KINEMATICS TO EQUIVALENT LINEAR DAMPING OF HELICOPTER BLADE HYDRAULIC DAMPER

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...

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Bibliographic Details
Published inApplied mathematics and mechanics Vol. 23; no. 8; pp. 922 - 930
Main Author HU Guo-cai(胡国才) XIANG Jin-wu(向锦武) ZHANG Xiao-gu(张晓谷)
Format Journal Article
LanguageEnglish
Published Institute of Aircraft Design and Research, Beijing University of,Aeronautics and Astronautics, Beijing 100083, P R China 01.08.2002
Subjects
blade
coupling
damper
damping
equivalent
helicopter
hydraulic
kinematic
linear
nonlinear
rotor
equivalent linear damping
hydraulic damper
nonlinear damping
kinematic coupling
helicopter rotor blade
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Summary: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.
Bibliography:O322.11
V275.1
31-1650/O1
ISSN:0253-4827
1573-2754
DOI:10.1007/BF02437797