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Investigation of the Effect of Blade Sweep on Rotor Vibratory LoadsThe effect of helicopter rotor blade planform sweep on rotor vibratory hub, blade, and control system loads has been analytically investigated. The importance of sweep angle, sweep initiation radius, flap bending stiffness and torsion bending stiffness is discussed. The mechanism by which sweep influences the vibratory hub loads is investigated.
Document ID
19840010128
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Tarzanin, F. J., Jr. (Boeing Vertol Co. Philadelphia, PA, United States)
Vlaminck, R. R. (Boeing Vertol Co. Philadelphia, PA, United States)
Date Acquired
September 4, 2013
Publication Date
October 1, 1983
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA-CR-166526
NAS 1.26:166526
AD-A135603
Report Number: NASA-CR-166526
Report Number: NAS 1.26:166526
Report Number: AD-A135603
Accession Number
84N18196
Funding Number(s)
CONTRACT_GRANT: NAS2-11151
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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