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Testing and evaluation of a stall-flutter-suppression system for helicopter rotors using individual-blade-controlThe development and testing of a feedback system designed to alleviate the violent blade first torsion mode oscillations associated with stall flutter are described. The system, based on previously developed M.I.T. Individual-Blade-Control hardware, employs blade-mounted accelerometers to sense torsional oscillations and feeds back rate informaton to increase the damping of the first torsion mode. A linear 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 analysis of experimental results. System performance in wind tunnel tests, both in hover and forward flight, is described, and evidence is given of the system's ability to provide substantial additional damping to stall-induced blade oscillations.
Document ID
19810020597
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Quackenbush, T. R. (Massachusetts Inst. of Tech. Cambridge, MA, United States)
Date Acquired
September 4, 2013
Publication Date
August 1, 1981
Subject Category
Aircraft Stability And Control
Report/Patent Number
NASA-CR-166233
ASRL-TR-196-3
Accession Number
81N29135
Funding Number(s)
CONTRACT_GRANT: NSG-2266
PROJECT: RTOP 505-42-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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