Abstract:

This paper presents a novel design method of the integrated guidance and control (IGC) for the solid missiles in the ascent phase subject to modeling uncertainties and external disturbances. Firstly, an ascent model considering the coupling between the guidance and control loops is established. Then it is converted to a control oriented ascent IGC design model based on the trajectory linearization method. The extended state observer (ESO) is adopted to timely estimate the modeling uncertainties and external disturbances to make them available for feedback. Based on the backstepping and feedback control methods, an active disturbance rejection based IGC design method is proposed. The stability analysis of the closed-loop system is provided in the framework of the Lyapunov stability theory. Finally, the numerical simulation demonstrates the efficiency and robustness of the proposed active disturbance rejection integrated guidance and control (ADRIGC).

Key words: Ascent integrated guidance and control model, Integrated guidance and control design, Extended state observer, Backstepping control, Solid missile