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Inertial dynamics of a general purpose rotorThe inertial dynamics of a fully articulated stiff rotor blade are derived with emphasis on equations that facilitate an organized programming approach for simulation applications. The model for the derivation includes hinge offset and six degrees of freedom for the rotor shaft. Results are compared with the flapping and lead-lag equations currently used in the Rotor Systems Research Aircraft simulation model and differences are analyzed.
Document ID
19790010745
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Duval, R. W. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 3, 2013
Publication Date
March 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-78557
A-7731
Accession Number
79N18916
Funding Number(s)
PROJECT: RTOP 518-51-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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