Nonlinear adaptive controller design for missile system with special uncertainties

The autopilot design for missiles with highly nonlinear in aerodynamics was presented. Firstly, a nonlinear model for the missile in the pitch plane was established. Then, the controller of the missile in the pitch plane, which was based on the nonlinear adaptive control theory with nussbaum gain, was proposed. A priori knowledge of the uncertainty bounds was not required, which enhanced the system robustness. It is proved that all the system signals were bounded and the tracking error converged to zero. Finally, Numerical simulation shows that the angel of attack can track the reference signal very well with system uncertainties. The simulation result verifies the correctness and effectiveness of the presented control law.