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Flap-lag equations of motion of rigid, articulated rotor blades with three hinge sequencesA derivation of coupled flap-lag equations of motion for a rigid articulated rotor with hinge springs and viscous dampers is reported. Three different flapping-lag-pitch hinge sequences are considered and the Lagrange method is used to derive the equations. The effects of the complete six degrees-of-freedom aircraft motions are included and all the inertia dynamic terms are retained; no small-angle assumptions are used in the development. Comparisons of the results with those available in the literature are made. Sources of terms missing in previous analyses, especially those of the inertia dynamics, are identified.
Document ID
19880003113
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Chen, Robert T. N. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 5, 2013
Publication Date
November 1, 1987
Subject Category
Aircraft Stability And Control
Report/Patent Number
NASA-TM-100023
A-87338
NAS 1.15:100023
Accession Number
88N12495
Funding Number(s)
PROJECT: RTOP 505-61-51
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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