Nonlinear dynamic autopilot design for the non-minimum phase missile

We propose some new ideas to stabilize the center of mass of high angle of attack missile. The dynamics which describe a missile are known to be non-minimum phase. We first design a controller arising from the local linear controllers integration with respect to some of the state variables. Next, from the concept of nonlinear asymptotic tracking problem, we propose to circumvent the non-minimum phase phenomenon and to achieve the stabilization by appropriately choosing some of the parameters which govern the exponential decaying of the error function between the output of the system under consideration and the reference desired function. These parameters satisfy the Hurwitz polynomial. In both cases, it is shown that the required missile performances are met