AEROSERVOELASTIC ANALYSIS AND ROBUST CONTROLLER SYNTHESIS by ALPER AKMEŞE

By ALPER AKMEŞE

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Once the generalized aerodynamic force matrix is obtained, it can be transformed into to state space and then be used in standard linear aeroelastic analyses. Using full and simplified versions of potential theory, the generalized aerodynamic force matrix of an aerodynamic surface can be calculated. There are package programs such as MSC/NASTRAN™ Flight Loads and Dynamics [49] that can calculate the generalized aerodynamic coefficient matrices of an aerodynamic surface using a thin airfoil assumption.

5) is obtained. Note that the system size, ns, is greater than the modal size, nm, ns ≥ nm. 5) where, [M'm], [C'm ], and [K'm] are of the order nmxnm, and [Φm] is nsxnm . 6) {ψ } : Generalized coordinates including the generalized coordinates of control surface and reduced generalized coordinates of the structural modes [Φδ] : nsxnδ matrix of vectors corresponding to the nδ deflections of the control surface δ, defined relative to the adjacent lifting surface. 1. Generalized Aerodynamic Force Matrices The aerodynamic forces can be derived by using panel methods and its simplified form slender body theory.

In addition to the contributions listed above, the following studies are also aimed in this thesis: - Employment of the flutter suppression method used in the controller synthesis procedure of Vipperman et al. [26] for airplane wings for a control actuation system with fully movable control surfaces. - 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.

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