An optimization procedure, based on the Aerodynamic Energy concept, is applied to the problem of flutter suppression using trailing-edge (T.E.) and tab control surfaces. A control law is assumed which allows the T.E.-Tab system to be driven by both linear and rotational sensors, and the optimum control law parameters are determined. Results are presented which indicate the capability of the T.E.-Tab control system to suppress flutter. A comparison is also made between the T.E.-Tab and the leading edge (L.E.)-T.E. control systems which shows their relative effectiveness together with some aspects connected to the realization of the control law.
Active flutter suppression using trailing-edge and tab control surfaces
AIAA, ASME, and SAE, Structures, Structural Dynamics, and Materials Conference ; 1975 ; Denver, CO
1975-05-01
Conference paper
No indication
English
Active wing flutter suppression using a trailing edge flap
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