Abstract
This paper demonstrates flight test results of disturbance attenuation of an aircraft by preview control, which was explained and its hardware-in-the-loop (HIL) simulation results were reported in a previous paper. The design methodology of preview control used here is the “two-stage” approach, in which a feedback gain is firstly designed by some standard design method and then a preview feedforward compensation is designed for the closed loop system. The flight test is carried out using a small research aircraft and a preview controller that alleviates disturbance response is designed for the aircraft model. Flight test results shows that the proposed preview controller alleviates vertical acceleration much better compared to the conventional feedback controller.
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