Robust control for missile with lateral jet and aerodynamic surfaces

In this paper, a robust blending control algorithm of tail fin and reaction jet of autopilot is proposed for the pitch control of a missile. The missile dynamic is a nonlinear system with uncertainties, which is existed in both aerodynamic force and moment generation terms in the equations of motion. The bound of the uncertainties are known, which is used to attenuate uncertainties by robust part in the control law, which guarantees the whole missile system with satisfying control performance both in transient state and steady state. The dual control allocator is designed to manipulate the tail fin and reaction jet of the missile work cooperatively when the deflection of aerodynamic rudder is in its limitation deflection and cannot supply enough torque via attitude deflection system. The stability analyses is provided for the closed-loop system in this paper. Finally, numerical simulations are given to illustrate the effectiveness of the proposed robust control law.