The problem of helicopter mechanical instability is considered for the case where one blade damper is inoperative. It is shown that if the hub is considered to be non‐isotropic the equations of motion have periodic coefficients which cannot be eliminated. However, if the hub
is isotropic the equations can be transformed to a rotating frame of reference and the periodic coefficients eliminated. The Floquet Transition Matrix method is shown to be an effective way of dealing with the nonisotropic hub and nonisotropic rotor situation. Time history calculations are
examined and shown to be inferior to the Floquet technique for determining system stability. A smearing technique used in the past for treating the one damper inoperative case is examined and shown to yield unconservative results. It is shown that instabilities which occur when one blade damper
is inoperative may consist of nearly pure blade motion or they may be similar to the classical mechanical instability.
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Document Type: Research Article
Langley Directorate, U.S. Army Air Mobility R&D Laboratory, NASA Langley Research Center, Hampton, Virginia
Publication date: 1974-10-01
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