Integrated design of missile guidance and control based on adaptive back-stepping sliding mode control

Since the missile dynamical system in the pitch plane is nonlinear, uncertain and non-matched, its integrated guidance and control is nontrivial. In order to cope with this problem, an adaptive back-stepping based sliding mode control algorithm is proposed in this paper. Firstly, the sliding surface of the virtual control variable is defined thanks to the strong robustness of sliding mode control. Secondly, it is highlighted that the calculation scales with the number of the virtual variables in back-stepping control. To deal with this problem, an adaptive sliding mode control is used to estimate the upper bound of the uncertainties and to simplify the control system design. The closed-loop stability has been proven based on Lyapunov theory. Finally, the simulation results have been reported to witness the validity of the algorithm, which show that the proposed approach can reject the target uncertainty and have a satisfactory control performance.