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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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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