By ALPER AKMEŞE
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Additional resources for AEROSERVOELASTIC ANALYSIS AND ROBUST CONTROLLER SYNTHESIS FOR FLUTTER SUPPRESSION OF AIR VEHICLE CONTROL ACTUATION SYSTEMS
However, the typical section model is applicable to lifting surfaces which has large aspect ratios, small sweeps, and smoothly varying cross sectional characteristics across span.
Fokker Company stated that the prototype wing showed no structural deficiencies. The only difference between the prototype wings and the production wing was the strengthening of the rear spar. This was ordered by the Luftwaffe, due to regulations for wire braced wings. Ironically, strengthening the rear spars moved the elastic axis backwards which resulted in a decrease of the divergence speed, which eventually caused the loss of Fokker D-8 aircrafts. After WW1 many flutter phenomena were seen; in 1923 wingaileron flutter was seen in von Berkel Seaplane (monoplane), which was solved by Baumhauer and Koning by mass-balancing the aileron.
This control is accomplished by various means. Some control types and their schematic illustrations are given in Figure 2. This study focuses on aerodynamic surface controllers. Although the aerodynamic surfaces have a general meaning, in this study it is used for airplane wings and missile control surfaces. Specifically, the current study applies to those in which the entire control surface is actuated in order to obtain the desired aerodynamic forces while there is no adjacent lifting surface.
AEROSERVOELASTIC ANALYSIS AND ROBUST CONTROLLER SYNTHESIS FOR FLUTTER SUPPRESSION OF AIR VEHICLE CONTROL ACTUATION SYSTEMS by ALPER AKMEŞE