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Means for controlling aerodynamically induced twistA control mechanism which provides active compensation for aerodynamically induced twist deformation of high aspect ratio wings consists of a torque tube, internal to each wing and rigidly attached near the tip of each wing, which is moved by an actuator located in the aircraft fuselage. As changes in the aerodynamic loads on the wings occur the torque tube is rotated to compensate for the induced wing twist.
Document ID
19820020403
Acquisition Source
Legacy CDMS
Document Type
Other - Patent
Authors
Elber, W. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
May 18, 1982
Subject Category
Aircraft Design, Testing And Performance
Accession Number
82N28279
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
NASA-CASE-LAR-12175-1|US-PATENT-4,330,100
Patent Application
US-PATENT-APPL-SN-079913

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