In this paper, an optimization technique for medium-high frequency dynamic problems based on Statistical Energy Analysis (SEA) method is presented. Using a SEA model, the subsystem energies are controlled by internal loss factors (ILF) and coupling loss factors (CLF), which in turn depend on the physical parameters of the subsystems. A preliminary sensitivity analysis of subsystem energy to CLFs is performed to select CLFs that are most effective on subsystem energies. Since the injected power depends not only on the external loads but on the physical parameters of the subsystems as well, it must be taken into account under certain conditions. This is accomplished in the optimization procedure, where approximate relationships between CLFs, injected power and physical parameters are derived. The approach is applied on a typical aeronautical structure: the cabin of a helicopter.
Vibroacoustic optimization using a statistical energy analysis model / Culla, Antonio; D'Ambrogio, Walter; Fregolent, Annalisa; Milana, Silvia. - In: JOURNAL OF SOUND AND VIBRATION. - ISSN 0022-460X. - STAMPA. - 375:(2016), pp. 102-114. [10.1016/j.jsv.2016.04.026]
Vibroacoustic optimization using a statistical energy analysis model
CULLA, Antonio;FREGOLENT, Annalisa;MILANA, SILVIA
2016
Abstract
In this paper, an optimization technique for medium-high frequency dynamic problems based on Statistical Energy Analysis (SEA) method is presented. Using a SEA model, the subsystem energies are controlled by internal loss factors (ILF) and coupling loss factors (CLF), which in turn depend on the physical parameters of the subsystems. A preliminary sensitivity analysis of subsystem energy to CLFs is performed to select CLFs that are most effective on subsystem energies. Since the injected power depends not only on the external loads but on the physical parameters of the subsystems as well, it must be taken into account under certain conditions. This is accomplished in the optimization procedure, where approximate relationships between CLFs, injected power and physical parameters are derived. The approach is applied on a typical aeronautical structure: the cabin of a helicopter.File | Dimensione | Formato | |
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