Minimum Eigenvalue Based Fault-Tolerant Adaptive 6-DOF Control for Spacecraft

An adaptive fault-tolerant control scheme based on minimum eigenvalue is proposed to solve the actuator failure problem of a six degree of freedom leader-follower spacecraft formation system to ensure the tracking performance of the tracking spacecraft against the position and attitude of the target spacecraft, in this paper. Firstly, a spacecraft attitude orbit integrated model based on dual quaternion is established, and control conditions and objectives are analyzed; Secondly, a dual control gain matrix is constructed and the minimum eigenvalue of the dual matrix is applied to manufacture the nominal control signal; Next, an adaptive law is devised to estimate the uncertainty caused by actuator faults and external disturbances; Finally, simulation verifies the effectiveness of this method.