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By ALPER AKMEŞE

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Extra info for AEROSERVOELASTIC ANALYSIS AND ROBUST CONTROLLER SYNTHESIS FOR FLUTTER SUPPRESSION OF AIR VEHICLE CONTROL ACTUATION SYSTEMS

Sample text

There exist few studies about the flutter suppression of missile control surfaces (fins). Aircraft wings are mainly composed of a fixed lifting surface and a trailing control surface (flap). Flutter suppression of the aircraft wing can be achieved by controlling the motion of the flap. On the other hand, fins are fully movable control surfaces without any adjacent lifting surface. The flutter suppression of the fin can be achieved via controlling the angular position of the fin shaft. This fact differentiates the aircraft wings and the fin.

There exist few studies about the flutter suppression of missile control surfaces (fins). Aircraft wings are mainly composed of a fixed lifting surface and a trailing control surface (flap). Flutter suppression of the aircraft wing can be achieved by controlling the motion of the flap. On the other hand, fins are fully movable control surfaces without any adjacent lifting surface. The flutter suppression of the fin can be achieved via controlling the angular position of the fin shaft. This fact differentiates the aircraft wings and the fin.

23], and in robust flutter analysis by Lind et al. [45]. However, in aeroservoelastic research studies, elastic models were not widely used. The reason is the introduction of large number of states due to elastic modeling, which increase the model complexity and computation time. From the papers surveyed, it is seen that elastic models were used for linear aeroservoelastic analysis problems but not in synthesis problems. Moreover, it is seen that, in the robust controller synthesis studies, only typical section models were used.

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