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

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The mechanism of potential flow flutter was understood by 1935, with the help of previous studies (1923-1929) and Theodorsen’s studies. During this period, many flutter phenomena occurred all over the world on different types of airplanes; air racers, transporters, observer airplanes, passenger airplanes, bombers, and attack airplanes. Different types of flutter were observed; wing-aileron, rudder-fuselage, tail, rudderfin, elevator- fuselage, and elevator-tab. With the increase incidences of flutter phenomenon, flight flutter tests became important.

Comparison of two different flutter suppression methods. - Aeroelastic and aeroservoelastic analysis with p and µ-methods. - Performance analyses of the aeroservoelastic systems. - Analysis of the effect of the backlash type of nonlinearity on the the aeroelastic. - Investigation of the effect of the backlash type of nonlinearity on the performance of the aeroservoelastic system with the controller mentioned above. 15 In order to develop the study in the control domain rather than the aerodynamics or structures domains the following limitations are applied in this study: - The structural part of the control actuation surface is modeled as a typical section model.

30], 20 in modern control studies by Mahesh et al. [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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