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Demonstration of an elastically coupled twist control concept for tilt rotor blade applicationThe purpose of this Note is to present results from an analytic/experimental study that investigated the potential for passively changing blade twist through the use of extension-twist coupling. A set of composite model rotor blades was manufactured from existing blade molds for a low-twist metal helicopter rotor blade, with a view toward establishing a preliminary proof concept for extension-twist-coupled rotor blades. Data were obtained in hover for both a ballasted and unballasted blade configuration in sea-level atmospheric conditions. Test data were compared with results obtained from a geometrically nonlinear analysis of a detailed finite element model of the rotor blade developed in MSC/NASTRAN.
Document ID
19950057399
Document Type
Reprint (Version printed in journal)
Authors
Lake, R. C. (NASA Langley Research Center Hampton, VA, United States)
Nixon, M. W. (NASA Langley Research Center Hampton, VA, United States)
Wilbur, M. L. (NASA Langley Research Center Hampton, VA, United States)
Singleton, J. D. (NASA Langley Research Center Hampton, VA, United States)
Mirick, P. H. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
July 1, 1994
Publication Information
Publication: AIAA Journal
Volume: 32
Issue: 7
ISSN: 0001-1452
Subject Category
AERODYNAMICS
Distribution Limits
Public
Copyright
Other