Actions for Investigation of the Effect of Blade Sweep on Rotor Vibratory Loads

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Investigation of the Effect of Blade Sweep on Rotor Vibratory Loads

Author
Tarzanin, F. J., Jr.
Published
Oct 1, 1983.
Physical Description
1 electronic document
Additional Creators
Vlaminck, R. R.
Online Version

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Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
The 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.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19840010128.
Accession ID: 84N18196.
NASA-CR-166526.
NAS 1.26:166526.
AD-A135603.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15708732