Nonlinear combined controller design and simulation based on block model for BTT missile

A combined control method is proposed based on nonlinear block model of missiles. A nonlinear control strategy for flight path angle and flight path azimuth angle is used to deal with the nonlinear non-affine system model. It is referred to as the dynamic feedback control that can guarantee that tracking errors converge exponentially. For attitude angles and angular velocities control, an adaptive backstepping and variable control method are used and parameter uncertainties, unmolded dynamic and uncertainties of control inputs are considered. Finally, nonlinear six-degree-of-freedom simulation results for BTT missile model are presented to demonstrate the effectiveness of proposed control law.