抄録
This paper describes a fault-tolerant flight control method using PID-SAC (Simple Adaptive Control) controller. The PID-SAC has the capability to adjust in an online manner not only feedback gains but also feedforward gains those are attached to a conventional PID flight controller. PID-SAC can generate control signals to follow the output signals of an original system with PID controller even if the dynamic characteristics change due to faults during flight. Numerical stimulations are investigated for a pitch angle controller of experimental aircraft MuPAL-a under the following fault cases; (1) decline in elevator effectiveness and (2) loss of longitudinal static stability. The simulations reveal the effectiveness of the proposing PID-SAC controller as a fault-tolerant flight controller.
