Abstract
The authors have been developed a flow-field integrated adaptive control system, which use in-flight surface pressure fields for real-time flight control. A simple mechanism for dynamic wind tunnel experiments is designed to run design and evaluation cycle for flow-field-integrated flight control. This system is not a tethered system using wires, but a yaw-rotatable seesaw system in which a lightweight aircraft model is supported from the lower fuselage at the center of gravity position. In this paper, we first explain the mechanism of the dynamic support system. The equations of motion of the model airplane on the support system are then derived, and the accuracy of the model is verified by comparing the motion quantities by simulation experiments and wind tunnel experiments. Once the validity of the simulation model is verified, the control law can be brushed up by repeating the design and verification cycle that goes back and forth between control law design by simulation and demonstration in the wind tunnel.
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