Abstract
Spacecraft subsystems with large surface area are exposed to the severe broadband random vibration during its launch. It has been empirically assumed that the dominant source of this random vibration environment is direct acoustic load inside a launch vehicle fairing rather than structural vibration transmission from attachment of spacecraft system. The design of spacecraft subsystems, therefore, have been normally verified by acoustic test. In recent years, however, as the needs for various space missions arise, the number of structurally-complex spacecrafts, which is hard to promptly find dominant source of random vibration, is on the increase. This provides the motivation for the present work in order to determine the critical random vibration environment for the design specification of spacecraft subsystems. In this paper, a simple calculation method employing joint acceptance and effective mass is proposed. This method is applied to small-sized satellite, and the validity of the method is experimentally shown for both diffuse acoustic and random vibration environments.
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