Abstract
Besides large-scale space missions, the spread of CubeSats for a variety of applications is increasingly requiring the development of systematic approaches for risk management. Being these applications are based on components with low TRL (Technology Readiness Level) or with limited performance data, it is required to define approaches which ensure a systematic perspective. This paper aims to present a reliability engineering approach based on FMECA (Failure Mode, Effects, and Criticality Analysis) to manage CubeSat reliability data and prioritize criticalities early in the design phase. The approach firstly proposes an alpha-numeric coding system to support the identification and labeling of failure modes for typical CubeSats’ items. Subsequently, each FMECA coefficient (i.e., Severity, Occurrence, Detectability) has been linked to the CubeSat’s structural properties, reducing subjectivity by means of techno-centric proxy indicators. The approach has been validated in the design phases of a 6-Units university CubeSat for the observation of M-Dwarf stars and binary systems. The performed analysis supported the design process and allowed to identify the major criticalities of the CubeSat design, as demonstrated in the extended case study included in the paper. The formalized method could be applied to design procedures for nano-satellites, as well as being expanded for research and development in a variety of space missions.
Highlights
Recent developments in microelectronics and additive manufacturing have enabled miniaturization of systems and the implementation of distributed architecture, leading to the development of constellation and mega-constellation of mini and nanosatellites [1]
By considering the heritage of the FMECA both in space operations and in other industrial domains, this paper proposes a semi-quantitative approach for developing a space-based FMECA to be used in the preliminary design of a CubeSat
The first step of an FMECA consists in structuring the problem, which means to build a model for representing the system at hand
Summary
Recent developments in microelectronics and additive manufacturing have enabled miniaturization of systems and the implementation of distributed architecture, leading to the development of constellation and mega-constellation of mini and nanosatellites [1] These new concepts imply the utilization of a standard, low cost satellite bus and the reduced reliability and decreased lifetime become acceptable considering that the huge number of orbiting satellites can overcome problems due to single satellite failure. This new paradigm in conceiving space missions sees a growing role for the reliability analysis in spacecraft design.
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