Testing of a Stall Flutter Suppression System for Helicopter Rotors Using Individual‐Blade‐Control
Abstract:The development and testing of a feedback system designed to alleviate rotor blade first torsion mode oscillations associated with stall flutter are described. The system emrdovs blade‐mounted sensors to detect torsional oscillations and provide feedback in order to increase the damping of the first torsional mode. A model of the blade and control system dynamics is developed and is used to give qualitative and quantitative guidance in the design process, as well as to aid in the analysis of experimental results. System performance in wind tunnel tests in forward flight is described, and experimental results show that the system can provide substantial additional damping to stall‐induced oscillations.
Document Type: Research Article
Affiliations: Massachusetts Institute of Technology, Cambridge, Massachusetts
Publication date: 1984-07-01
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