NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Flutter suppression digital control law design and testing for the AFW wind tunnel modelDesign of a control law for simultaneously suppressing the symmetric and antisymmetric flutter modes of a sting mounted fixed-in-roll aeroelastic wind tunnel model is described. The flutter suppression control law was designed using linear quadratic Gaussian theory, and involved control law order reduction, a gain root-locus study and use of previous experimental results. A 23 percent increase in the open-loop flutter dynamic pressure was demonstrated during the wind tunnel test. Rapid roll maneuvers at 11 percent above the symmetric flutter boundary were also performed when the model was in a free-to-roll configuration.
Document ID
19920053044
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mukhopadhyay, Vivek
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 92-2095
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
92A35668
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available