Integrated guidance and control with partial state constraints and actuator faults

•Partial state constraints and actuator faults are simultaneously addressed in integrated guidance and control.•The barrier Lyapunov function and modified saturation function are employed to prevent the attack angle, sideslip angle and velocity deflection angle from violating the constraints.•An auxiliary system is constructed to remove the adverse effects that caused by the modified saturation function. The adaptive laws are constructed to deal with actuator faults and uncertainties in the IGC system.•It is theoretical shown that all signals in closed-loop system are bounded while the state constraints are not violated in presence of actuator faults. In this paper, a novel adaptive integrated guidance and control (IGC) scheme is proposed for skid-to-turn (STT) missile with partial state constraints and actuator faults. Considering the strict-feedback form of the IGC model, the dynamic surface control (DSC) approach is adopted to design the IGC scheme. To prevent the attack angle, sideslip angle and velocity deflection angle from violating the constraints, the barrier Lyapunov function (BLF) and modified saturation function are employed in the IGC design procedure. Moreover, an auxiliary system is constructed to remove the adverse effects that caused by the modified saturation function. The adaptive laws are constructed to estimate the actuation effectiveness of actuators and the upper bounds of lumped uncertainties in the IGC model. It is theoretically shown that all signals in the closed-loop system are bounded while the state constraints are not violated in presence of actuator faults and uncertainties. Numerical simulation results are presented to verify the effectiveness and robustness of the proposed IGC scheme.