Control of component excitation generated structure‐borne noise transmission into a rotorcraft cabin, such a s from rotor vibration imbalance, transmission excitations or auxiliary equipment induced vibrations, can he studied empirically via accelerance characterization of the
system components and application of appropriate component coupling procedures. The present study was aimed at demonstrating the usefulness of such accelerance modeling techniques as applied to a Bell 206B rotorcraft. Simulated rotor excitations were applied to the assembled rotorcraft system
to provide baseline structure‐borne noise transmission data. Thereafter, accelerance tests of the system components were carried out to provide a data base from which system component coupling studies were carried out. Results presented demonstrate the level of expected accuracy in
predicted structure‐borne noise transmission from the component coupled model. Compliance was then analytically introduced at attachments between system components to evaluate the level of expected structure‐borne noise isolation for a given level of joint compliance.
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Document Type: Research Article
Southwest Research Institute, San Antonio, Texas
Publication date: 1999-07-01
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