Abstract
This paper investigates the tracking control problem for the air-to-air missile with lateral thrusters and aerodynamic surfaces. An integral sliding mode manifold which is suitable for solving the problem of the input constraint is first given based on the saturation function. By using the integral sliding mode manifold, a finite-time controller without singularity is designed to deal with the input saturation and bounded disturbances. Then, the control moment is mapped to the control commands for the aerodynamic deflector and thrust engine array respectively, by using the dynamic control allocation. Finally, theoretical analysis and numerical simulations are presented to prove that the robust controller can make the missile follow a reference signal in finite time.
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