Nonlinear missile autopilot design via three loop topology and time-delay adaptation scheme

In this paper, a new missile acceleration controller is proposed, based on the three loop control structure with the feedback linearization control law and time-delay adaptive law. In order to avoid the nonminimum characteristics of conventional missile systems, an approximate system and three loop topology are considered. Under this control structure, the feedback linearization methodology is applied to relieve difficulties of aerodynamic nonlinearity. Finally, this controller is augmented by the time-delay adaptation scheme to compensate for the model uncertainties. The performance of proposed autopilot is tested using a nonlinear missile model with uncertainties, by imposing step commands.