The design 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 it also 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.
Flutter Suppression Digital Control Law Design and Testing for the AFW Wind Tunnel Model
1994
15 pages
Report
No indication
English
Flutter Suppression Digital Control Law Design and Testing for the AFW Wind-Tunnel Model
British Library Conference Proceedings | 1994
|