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Demonstration of an elastically coupled twist control concept for tilt rotor blade applicationThis study demonstrated the feasibility of passive blade twist control for composite rotor blades. Hover testing of the set of blades produced maximum twist changes of 2.54 degrees for the unballasted blade configuration and 5.24 degrees for the ballasted blade configuration. These results compared well with those obtained from a detailed finite element analysis model of the rotor blade, which yielded maximum twists of 3.02 and 5.61 degrees for the unballasted and ballasted blade configurations, respectively.
Document ID
19950036583
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Lake, R. C.
Nixon, M. W.
Wilbur, M. L.
Singleton, J. D.
Mirick, P. H.
Date Acquired
August 16, 2013
Publication Date
July 1, 1994
Publication Information
Publication: AIAA Journal
Volume: 32
Issue: 7
ISSN: 0001-1452
Subject Category
Aircraft Propulsion And Power
Accession Number
95A68182
Distribution Limits
Public
Copyright
Other

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