Estimation of fuselage vibration is one of the most challening tasks in the rotorcraft field since it requires sophisticated mathematical modeling of both airframe and rotor and specialized analysis procedure. Currently, most studies incorporate either simple rotor modeling or simple body modeling to predict vibration. The present study is directed towards assessing various mathematical models of rotors and airframe to develop rotor-body coupled vibration analysis. For this purpose, five rotor models ranging from simple rigid flap model to nonlinear coupled flap-lag-torsion-axial elastic model, and three airframe models ranging from six degree of freedom rigid model to distributed elastic line model are formulated. The rotor-body coupling is achieved through an implicit procedure. For numerical study, an elastic line model of the Bell Huey AH-1G helicopter airframe is coupled to a four bladed soft-inplane hingeless rotor. The study shows simpler blade models over-predict vibration along vertical, pitch, and roll directions and under-predict vibration along longitudinal, lateral, and yaw directions. For proper accounting of rotor-body coupling effects, it is necessary to include a detailed elastic model of airframe.
Effect of modeling techniques in the coupled rotor-body vibration analysis
Die Auswirkungen der Auslegungstechnik in der gekoppelten Schwingungsanalyse von Rotor und Flugzeugrumpf
1993
13 Seiten, 4 Bilder, 21 Quellen
Aufsatz (Konferenz)
Englisch
Coupled rotor/airframe vibration analysis
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