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This paper presents a systematic methodology for the synthesis of global gain-scheduled controllers for nonlinear time-varying systems. A controller of this type is used to compute the pitch-axis autopilot of an air-air missile. The missile model used is considered a benchmark for testing autopilot controllers in the academic and industrial communities. The missile's dynamics are linearized at a small set of operating points for which proportionalintegral/proportional-type controllers are designed, to shape the frequency response of the linear plants' dynamics. A new set of operating points is computed afterward using the connection between the gap metric and the H 1 loopshaping theory. Then, reduced-order, static, H 1 loop-shaping controllers are designed for this set of points using linear matrix inequality optimization techniques. Finally, the global gain-scheduled controller is obtained by interpolating the proportional-integral/proportional and the loop-shaping controllers' gains over the missile's flight envelope. The simulation results given show the generality and effectiveness of the proposed control strategy in terms of the operating point selection, stability, performance and robustness, of the closed loop.

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This paper presents a study concerning a class of fin-guided spin-stabilized 155 mm ammunitions with CCF (Course Correction Fuzes). The 7 Degrees of Freedom (DoF) non linear equations are written in a non-rolling body frame. Aerodynamics coefficients are being determined by wind tunnel tests and CFD simulations. The paper reports results concerning equilibrium manifold computation, equilibrium accelerations, LPV modeling and stability analysis. Nomenclature