Abstract:

Based on active disturbance rejection control and the backstepping-sliding mode design method, an integrated guidance and control design is proposed for missiles during the terminal course. The integrated model is formulated as a block-strictfeedback nonlinear system, in which modeling errors and target maneuvers are viewed as unknown uncertainties. An extended state observer is developed to estimate and compensate the impact from uncertainties and disturbances. A backstepping-sliding mode controller is proposed to realize the attitude control. Simulation results show that, with the application of the proposed method, small miss distances are achieved, and the system is robust against system uncertainties and disturbances.