Abstract
The purpose of this study is to solve the vibration responses of spacecraft equipment structures, especially light weight rigid panels, such as a solar array paddle or an antenna, excited by an low frequency acoustical noise field. In this paper, first, the direct loading pressure to the structure in a random sound field, is derived and the response calculation method using FEM is proposed. Second, the derivation of the direct loading pressure to the structure is experimentally verified, using a honeycomb panel of which the edge was bolted to a stand, in the steady-state sound pressure field. Finally, experimental results of the acceleration reponses of the panel in the random sound field are found to agree with the simulation results of this proposed calculation method. And the simulation results of the usual frequency response method contain a high degree of error compared with the results of the new method.
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