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The focus of the present master thesis is the automation of an existing controller design for a missile using two aerodynamic actuating systems. The motivation is to evaluate more missile concepts in a shorter period of time. The option used is trimming and linearization of a highly nonlinear missile at speci c conditions. According to these conditions, either a two-dimensional operating point grid dened by Mach number and height or three-dimensional operating point grid dened by Mach number, height and angle of attack is generated for the whole operating range of the missile. The controllers are designed at these points using convex optimization. The convex set denes the pole placement area which is constrained by linear matrix inequalities according to the dynamic behavior of the missile at the operating point conditions. These controllers describe a validity area where the missile can be stabilized. This area consists all neighboring operating points and denes therefore the grid density which can dier at specic regions of the operating range. Controlling the missile to the target makes it necessary to apply gain-scheduling in order to get the manipulated variable by interpolation of adjacent operating points. During this blending of the controllers a problem called windup can occur when an actuator is saturated.
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