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Levels of Vibration Impact during Testing of Spacecraft Avionics Equipment

The tightening of avionics lifetime and reliability requirements necessitates a profound and efficient experimental method. At the same time, the not infrequent absence of even two equipment samples for conducting tests (considering the variation of properties of materials and technological processes) makes the problem of confirming hardware strength characteristics difficult to solve. The present paper describes a methodology for vibration tests of spacecraft onboard electronics that allows us to reliably confirm the strength of a random sample of the given equipment based on the testing of a single test specimen. Safety margins for different stages of equipment vibration testing are determined. These margins are necessary to ensure the given probability of design defect detection. The proposed methodology is compared with current foreign regulatory documents dedicated to testing spacecraft onboard electronics. The proposed method allows a flexible approach to the selection of vibration test levels since it takes into account the design features of the equipment affecting strength spread from sample to sample during the determination of the scope of required tests.