A conventional finite element model of an aircraft wheel and brake is extended to include forces responsible for friction-induced noise. Responses to aircraft brake vibration modes change the normal force across the brake friction interfaces, and consquently the friction forces. The resulting friction force variations are assembled in the form of supplemental stiffness matrix and added to the finite element model. Complex eigenvalue analysis that includes the friction force variations provides frequency and mode shape information, as well as an assessment of the predicted mode stability. A predicted unstable vibration mode compares very well to operating mode shape data determined from instrumented tests. Hardware modifikations to reduce a brake noice in an aircraft cabin were based on beneficial trends found from exercising the model. Implementation of the hardware modifikations on the aircraft succesfully suppressed the noice.
Complex eigenvalue analyses applied to an aircraft brake vibration problem
Komplexe Eigenwertanalyse, angewandt auf ein Schwingungsproblem bei Flugzeugbremsen
1995
8 Seiten, 12 Bilder, 10 Quellen
Conference paper
English
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