Flight test of fault-tolerant flight control system using simple adaptive control with PID controller

Abstract

Purpose This paper aims to demonstrate the effectiveness of a fault-tolerant flight control method by using simple adaptive control (SAC) with PID controller. Design/methodology/approach Numerical simulations and flight tests are executed for pitch angle and roll angle control of research aircraft MuPAL-α under the following fault cases: sudden reduction in aileron effectiveness, sudden reduction in elevator effectiveness and loss of longitudinal static stability. Findings The simulations and flight tests reveal the effectiveness of the proposed SAC with PID controller as a fault-tolerant flight controller. Practical implications This research includes implications for the development of vehicles’ robustness. Originality/value This study proposes novel SAC-based flight controller and actually demonstrates the effectiveness by flight test.