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Helicopter rotor blade design for minimum vibrationThe importance of blade design parameters in rotor vibratory response and the design of a minimum vibration blade based upon this understanding are examined. Various design approaches are examined for a 4 bladed articulated rotor operating at a high speed flight condition. Blade modal shaping, frequency placement, structural and aerodynamic coupling, and intermodal cancellation are investigated to systematically identify and evaluate blade design parameters that influence blade airloads, blade modal response, hub loads, and fuselage vibration. The relative contributions of the various components of blade force excitation and response to the vibratory hub loads transmitted to the fuselage are determined in order to isolate primary candidates for vibration alleviation. A blade design is achieved which reduces the predicted fuselage vibration from the baseline blade by approximately one half. Blade designs are developed that offer significant reductions in vibration (and fatigue stresses) without resorting to special vibration alleviation devices, radical blade geometries, or weight penalties.
Document ID
19850001725
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Taylor, R. B.
(United Technologies Research Center East Hartford, CT, United States)
Date Acquired
September 5, 2013
Publication Date
October 1, 1984
Publication Information
Publisher: NASA
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA-CR-3825
AVSCOM-TR-84-A-2
R33-915783-27
NAS 1.26:3825
Accession Number
85N10032
Funding Number(s)
CONTRACT_GRANT: NAS2-11025
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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