A design procedure is presented for the installation of simple pendulums on the blades of a helicopter rotor to suppress the root reactions. The procedure consists of a frequency response analysis for a hingeless rotor blade excited by a harmonic variation of spanwise airload distributions during forward flight, as well as a concentrated load at the tip. The structural modeling of the blade provides for elastic degrees of freedom in flap and lead-lag bending plus torsion. Simple flap and lead-lag pendulums are considered individually. Using a rational order scheme, the general nonlinear equations of motion are linearized. A quasi-steady aerodynamic representation is used in the formation of the airloads. The solution of the system equations derives from their representation as a transfer matrix. The results include the effect of pendulum tuning on the minimization of the hub reactions.
Helicopter vibration suppression using simple pendulum absorbers on the rotor blade
National Specialists Meeting on Helicopter Vibration ; 1981 ; Hartford, CT
1981-11-01
Conference paper
No indication
English
Helicopter vibration suppression using simple pendulum absorbers on the rotor blade
Tema Archive | 1982
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