Adaptive Support of an Aircraft Panel

TL;DRAbstract

The vibro-acoustic behavior of large lightweight structures such as aircraft fuselage has to be tested, especially to improve active and passive noise control means. Acoustic transmission laboratories with reverberant and anechoic rooms supply reliable test conditions for aircraft panels of a size up to several square meters. Shock mounts support these panels to realize free or pinned boundary conditions with minor damping, which is sufficient at high frequencies. At low frequencies, the vibration of the whole fuselage has to be considered. Therefore the support of the panel under test should provide the same dynamic impedance as the fuselage to which the panel would be connected in the aircraft. This frequency-dependent boundary condition can be realized by an adaptive support. The paper describes a numerical investigation of this supported panel which should behave like integrated into an aircraft fuselage.

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