Abstract
Active vibration control for a 25 %-scale model of a high-speed compound unmanned rotorcraft was experimentally studied. The compound rotorcraft uses wings, propellers, and a lift-offset coaxial rotor system with two blades per rotor. A small-scale airframe structure was manufactured using aluminum and steel and appropriately represents the dynamic similarity of the full-scale model. A ground vibration test (GVT) was used in this experimental work. An active vibration control system (AVCS) using two force generators and three accelerometers was applied for the active vibration control of the small-scale airframe model. Three accelerometers that measure acceleration signals in the vertical direction of the airframe are located at specific airframe locations: the remote cockpit unit, wing root, and wing tip. A 2P rotor hub pitch moment that produces a linear force generator was used to excite the airframe structure. The AVCS using the Fx-LMS algorithm was implemented using MATLAB Simulink, dSPACE ControlDesk, and MicrolabBox. This experimental study shows that the vibration responses of the airframe in the vertical direction at the specific airframe positions are reduced by 47.54 % ~ 84.67 %, and the test results compare reasonably with the simulation results.
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