Abstract:Acceleration control of highly agile, aerodynamically-controlled missiles is a well-known non-minimum phase control problem. This problem is revisited here for a planar tailcontrolled generic missile, and a globally stable nonlinear autopilot command structure is synthesized to maximize performance. For the first time the non-minimum phase characteristics of the vehicle are addressed by making no modification to the output definition by inducing an inherent time scale separation in the closed-loop dynamics. Un… Show more
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