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In spacecraft development, acoustically induced vibration of spacecraft equipment panel is one of the critical design consideration. The prediction of the vibroacoustics is necessary to specify the environment during spacecraft launch. Joint acceptance which is based on the integral calculus with the mode shape has been proposed for the prediction method by the authors. However, the prediction accuracy of the approach is poor for the complex structure in high frequency because of the uncertainty in the mathematical model. This paper is concerned with the approach using simplified joint acceptance employing radiation efficiency and spacecraft panel mass, not based on the integral calculus. The approach is applied to diffuse acoustical excitation of spacecraft panel, and is compared with the results of acoustic excitation test, conventional approach of joint acceptance and SEA. It is shown that the result provide good predictions in high frequency.

Vibroacoustic Analysis of Spacecraft Panel Using Simplified Joint Acceptance Employing Radiation Efficiency and Panel Mass