Two flutter suppression control laws have been synthesized, implemented, and tested on a low-speed aeroelastic wing model of a DC-10 derivative. The methodology used to design the control laws is described. Both control laws demonstrated increases in flutter speed in excess of 25 percent above the passive wing flutter speed. The effect of variations in gain and phase on the closed-loop performance was measured and is compared with analytical predictions. In general, the analytical results are in good agreement with experimental data.
Wind-tunnel evaluation of NASA developed control laws for flutter suppression on a DC-10 derivative wing
Conference on Structures, Structural Dynamics and Materials ; 1981 ; Atlanta, GA
1981-01-01
Miscellaneous
No indication
English