Actuator Fault‐Tolerant Adaptive Nonsingular Predefined‐Time Guidance Law With Terminal Angle Constraint and Input Saturation

This study focuses on the terminal angle constrained interception of maneuvering target by missile in three‐dimensional (3D) coupled environment. Considering actuator failures and input saturation, an adaptive non‐singular terminal sliding mode guidance law is proposed based on the predefined‐time convergence theory. Its design features an adjustable convergence time parameter. First, an adaptive guidance law is developed, the states can converge to zero in the predefined time under ideal conditions. Subsequently, based on this foundation, another anti‐saturation fault‐tolerant guidance law is developed, which can realize the interception of targets in scenarios involving actuator failure and input saturation. Comprehensive simulation experiments validate the efficacy of the proposed algorithms.