Secure Adaptive Trajectory Tracking Control for Spacecraft Attitude Systems With Unknown FDI Attacks and Disturbance

This article considers the secure adaptive trajectory tracking control problem for spacecraft attitude systems with unknown false data injection (FDI) attacks and disturbance. The kinematics and dynamics equations of a 3‐1‐2 rotation sequence using Euler angles are given to construct a model of the spacecraft attitude systems. A recursive scheme is developed to design virtual and actual control laws. Meanwhile, a parameter adaptive law is utilized to estimate the upper bound of the attack signal. The proposed control method can guarantee that the tracking error of attitude angles converges to a small region of the origin, and a Lyapunov function is utilized to prove the stability of the spacecraft attitude closed‐loop systems. Finally, simulation results are provided to verify the effectiveness of the developed approach.