Wind tunnel testing of a Mach-scaled rotor model with trailing-edge flaps

摘要: This paper presents the wind tunnel testing of a four-bladed Mach-scaled rotor model with piezoelectric bender actuated trailing-edge flaps. Correctly phased, this flap motion can be used for active suppression vibratory hub loads. First, University Maryland Advanced Rotorcraft Code was to conduct parametric study determine optimal sizing and location as well required deflection amplitudes. Next, simplified analysis which explicitly models actuator dynamics design multi-layer configuration that is capable achieving deflections. Based on above studies, matched set four blades piezo-bender flaps were fabricated in-house. operated using one-seventh scale Bell-412 hub. Finally, system tested in forward flight Glenn L Martin tunnel. These tests consisted open-loop single-frequency at different speeds collective settings. Some preliminary closed-loop neural network control algorithm also conducted. Presented American Helicopter Society 56th Annual Forum, Virginia Beach, VA. Copyright 2000 by Society, Inc. All rights reserved.