Download PDF by ALPER AKMEŞE: AEROSERVOELASTIC ANALYSIS AND ROBUST CONTROLLER SYNTHESIS

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By ALPER AKMEŞE

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On the other hand, it is also possible to define uncertainties for flight parameters and a robust controller can be synthesized considering these uncertainties. Waszak [27] performed a similar study. In that study, the uncertainty of the aeroelastic system was derived by applying a disturbance to the dynamic pressure. At the controller synthesis step, the aeroelastic system uncertainty was included, hence the disturbance to dynamic pressure was included indirectly. However, a controller synthesis procedure that directly includes the dynamic pressure disturbance at the controller synthesis step was not come across during the survey of the open literature.

However, the limit cycle oscillation is still an undesired phenomenon, since it decreases the remaining fatigue life of the structure. - The flutter speed is a function of: o Airplane structural parameters such as ƒ Geometry, mass distribution, stiffness distribution, and structural damping o Flight parameters such as ƒ Airspeed, altitude, Mach number, and angle-of-attack Buffeting, B. ” Dynamic response, Z. ” Aeroelastic effects on stability, (S/D)SA. ” Load distribution, L. ” Divergence, D. ” Divergence is also named as zero frequency flutter.

55]. In the finite element method, the wing is meshed with sufficient amount of elements, such that the required minimum number of elastic modes can be represented. For the modeling of the wing, a small number of lowest modes of the structural system should be kept for the purpose of performance as well as some additional number of modes in the crossover frequency range of the system should be kept to ensure the close loop stability. For the modeling of the control surface, less number of modes can be kept since its structure is simpler than a wing structure.

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AEROSERVOELASTIC ANALYSIS AND ROBUST CONTROLLER SYNTHESIS FOR FLUTTER SUPPRESSION OF AIR VEHICLE CONTROL ACTUATION SYSTEMS by ALPER AKMEŞE


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