CubeSat-Life Ground Test Facility: Ground Facility to Simulate a CubeSat Environment for the Cultivation of Ideotype Tomato Plants

Marzioli, Paolo; Delfini, Andrea; Gugliermetti, Luca; Santoni, Fábio; Bisegna, Fablo; Nardi, Luca; Benvenuto, Eugenio; Massa, Silvia; Bennici, Elisabetta

doi:10.1109/metroaerospace.2018.8453567

Cited by 3 publications

(1 citation statement)

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“…The designed 6-Units (6U, approximately 20 × 10 × 30 cm, [36]) CubeSat is equipped with a reflecting telescope in Ritchey Chrétien configuration. Part of the designed provisions on the bus components are heritage of former and current CubeSat development and operations projects managed by Sapienza University of Rome ( [37][38][39]), whose involvement into the spacecraft development field of research usually brings to the launch of a new CubeSat every few years [33]. The CubeSat has been designed according to a set of preliminary mission requirements, generated by the observables binary systems magnitude, distance and latitude (with respect to the galactic plane).…”

Section: Step 1: Spec Cubesat Design and Functional Block Diagrammentioning

confidence: 99%

A Reliability Engineering Approach for Managing Risks in CubeSats

et al. 2018

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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.

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Section: Step 1: Spec Cubesat Design and Functional Block Diagrammentioning

confidence: 99%