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In TÜBİTAK-SAGE, a leading research and development institute in the defense industry of Turkey, various studies were performed about aeroelasticity since the beginning of the 1990s. Among these studies, Tanrıkulu [8, 9], Kuran et al. [10, 11], Durak [12], Yıldız [13], Sever [14] Pehlivanoğlu et al. [15], Akmeşe et al. [16], and Ünal [17] performed aeroelastic analysis of rocket and missile fins including linear and nonlinear structural models. In early 1990s, an introductory study was also conducted by Tanrıkulu [18] about aeroservoelasticity without performing a detailed investigation.

The derived aerodynamic forces will contain an implicit or explicit irrational dependence on reduced frequency. To be compatible with most control design approaches, the aerodynamic forces are fit by explicit rational functions of the states of the system by the following two-step process: 27 a) Identify the structural motions for which the aerodynamic effects will be calculated. Then calculate the unsteady aerodynamic forces for these modal motions, control surface motions, or gust inputs. 8) where ω : frequency b : semichord length of the wing U : airspeed and over the frequency range of interest.

If the people who asked these questions are alive, the answer of the first question is yes. The answer of the second question is in the field of aeroelasticity. ”Aeroelasticity is the study of the effect of aerodynamic forces on elastic bodies” [1]. In Figure 1, the aeroelastic triangle of forces introduced by Collar is given [ 2 ]. This figure also describes the classification of aeroelasticity problems. In Figure 1, A, E, and I represent the Aerodynamic, Elastic, and Inertial forces, respectively.

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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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