Demonstration of an elastically coupled twist control concept for tilt rotor blade application

This 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...

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Bibliographic Details
Published in:AIAA journal 1994-07, Vol.32 (7), p.1549-1551
Main Authors: Lake, R. C, Nixon, M. W, Wilbur, M. L, Singleton, J. D, Mirick, P. H
Format: Article
Language:English
Subjects:
Aerodynamics
Aircraft
Aircraft Propulsion And Power
Composite materials
Exact sciences and technology
Fundamental areas of phenomenology (including applications)
Physics
Solid mechanics
Static elasticity
Static elasticity (thermoelasticity...)
Structural and continuum mechanics
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Summary:This 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.
ISSN:0001-1452
1533-385X
DOI:10.2514/3.12232