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On methods for application of harmonic controlThe paper presents data which confirm the effectiveness of higher harmonic blade pitch control in substantially reducing helicopter rotor vibratory hub loads. The data are the result of recent tests on a 2.7-m model conducted in the Langley Research Center's transonic dynamics wind tunnel. Several predictive analyses developed in support of the NASA program are shown capable of accurately predicting both amplitude and phase of the higher harmonic control input required to nullify a single 4/rev force or moment input. The use of multiple blade feathering inputs in the design of a flightworthy higher harmonic control system is discussed.
Document ID
19790034644
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Wood, E. R.
(Hughes Helicopters Culver City, CA, United States)
Powers, R. W.
(Hughes Helicopters Culver City, Calif., United States)
Hammond, C. E.
(U.S. Army, Research and Technology Laboratories, Hampton Va., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1978
Subject Category
Aircraft Design, Testing And Performance
Meeting Information
Meeting: European Rotorcraft and Powered Lift Aircraft Forum
Location: Stresa
Country: Italy
Start Date: September 13, 1978
End Date: September 15, 1978
Accession Number
79A18657
Funding Number(s)
CONTRACT_GRANT: NAS1-14522
Distribution Limits
Public
Copyright
Other

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