The recent interests in the necessity of high maneuverability and vertical launching triggered namely the unconventional control design techniques that are effective at high angle of attack flight regimes. Hence, most of the tactical missile configurations use conventional aerodynamic controls together with the thrust vectoring controls. In this study, a numerical optimization approach to satisfy the rapid turnover maneuver of a generic vertical launch surface to air missile (VLSAM), with tail fins and jet vanes, is described. Since the stated problem inherently requires the missile to perform maneuvering at high angles of attack, it has a challenging nonlinear system dynamics originating from the flight mechanics equations and the control limitations. The optimal guidance commands are computed with real coded genetic algorithm and the results show that the rapid turnover can optimally be conducted considering the detailed physical properties of the given missile model example. In this paper, the numerical optimization algorithms are implemented directly on the detailed nonlinear 6 degree of freedom (DoF) flight mechanics model with hybrid control allocation. For that reason, this study is believed to have importance when compared with the former similar optimization studies within the literature in which most of the plant modeling efforts are kept considerably limited.
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