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Flutter suppression for the Active Flexible Wing - Control system design and experimental validationThe synthesis and experimental validation of a control law for an active flutter suppression system for the Active Flexible Wing wind-tunnel model is presented. The design was accomplished with traditional root locus and Nyquist methods using interactive computer graphics tools and with extensive use of simulation-based analysis. The design approach relied on a fundamental understanding of the flutter mechanism to formulate understanding of the flutter mechanism to formulate a simple control law structure. Experimentally, the flutter suppression controller succeeded in simultaneous suppression of two flutter modes, significantly increasing the flutter dynamic pressure despite errors in the design model. The flutter suppression controller was also successfully operated in combination with a rolling maneuver controller to perform flutter suppression during rapid rolling maneuvers.
Document ID
19920053042
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Waszak, M. R.
(NASA Langley Research Center Hampton, VA, United States)
Srinathkumar, S.
(National Aeronautical Laboratory Bangalore, India)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 92-2097
Meeting Information
Meeting: AIAA Dynamics Specialists Conference
Location: Dallas, TX
Country: United States
Start Date: April 16, 1992
End Date: April 17, 1992
Accession Number
92A35666
Distribution Limits
Public
Copyright
Other

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