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A demonstration of passive blade twist control using extension-twist couplingThe feasibility of passive blade twist control using an extension-twist-coupled composite rotor blade design has been demonstrated. A set of low-twist model-scale helicopter rotor blades has been manufactured from existing molds with the objective of demonstrating this control concept. Hover testing of the set of blades demonstrated maximum twist changes of 5.24 deg for the ballasted blade configuration, and 2.54 deg for the unballasted configurations in the atmospheric test condition. These results compared well with those obtained from a detailed FEM analysis of the rotor blade. Aerodynamic-induced effects on the blade elastic twist were found to be minimal.
Document ID
19920051734
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
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; U.S. Army, Aerostructures Directorate, Hampton VA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 92-2468
Report Number: AIAA PAPER 92-2468
Meeting Information
Meeting: AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Location: Dallas, TX
Country: United States
Start Date: April 13, 1992
End Date: April 15, 1992
Accession Number
92A34358
Distribution Limits
Public
Copyright
Other

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