Abstract
The paper generalizes results of introducing procedures of reliability design and technological analysis (RDTA) in the one-time actuation mechanisms of the spacecraft rotary structures (hereinafter referred to as the mechanisms). It provides principles of the mechanisms design and examples of establishing the design documentation requirements in their design process. The differences between processes of the mechanism design and construction are presented, and examples of design and technological factors that could lead to potential failures of such mechanisms are given. Principles of substantiating the spacecraft onboard equipment performance and reliability are considered. Commonality and differences in substantiating performance and reliability of mechanisms and of other onboard equipment of spacecraft are provided. As a result of the RDTA introduction, it was revealed that methods were missing in substantiating performance and reliability of the products for various purposes that were different in form. Only the content of engineering tasks that ensured fulfillment of their service purpose was varying. Moreover, solutions to such problems could be verified using the formalized procedures in reliability design and technological analysis.
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