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This paper aims to demonstrate the effectiveness of a fault-tolerant flight control method by using simple adaptive control (SAC) with PID controller.

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.

The simulations and flight tests reveal the effectiveness of the proposed SAC with PID controller as a fault-tolerant flight controller.

This research includes implications for the development of vehicles’ robustness.

This study proposes novel SAC-based flight controller and actually demonstrates the effectiveness by flight test.