Abstract
Pilot-Induced Oscillation (PIO) was encountered in the company flight test of the T-2CCV research vehicle. The main cause of the roll PIO was due to unexpected large pilot input and to increased delay of the aircraft response by its large pilot input. The delay of roll response has much difference between with large input and with small input. That is why the flight control system falls into nonlinear system by actuator rate limit in case of controlling the aircraft with large pilot input. This paper shows analysis of the characteristics of the PIO and its improvement.
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