Survey on the implementation and reliability of CubeSat electrical bus interfaces

Journal article (2016)

Authors

J. Bouwmeester Space Systems Egineering
M Langer Technische Universität München
E.K.A. Gill Space Engineering
Research Group
Space Systems Egineering
Copyright: © 2016 J. Bouwmeester, M Langer, E.K.A. Gill
DOI
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https://doi.org/10.1007/s12567-016-0138-0
CubeSat Reliability Wiring harness Power distribution Data bus
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Published Date

2016

Language

English

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Research Group

Space Systems Egineering

Abstract

This paper provides results and conclusions on a survey on the implementation and reliability aspects of CubeSat bus interfaces, with an emphasis on the data bus and power distribution. It provides recommendations for a future CubeSat bus standard. The survey is based on a literature study and a questionnaire representing 60 launched CubeSats and 44 to be launched CubeSats. It is found that the bus interfaces are not the main driver for mission failures. However, it is concluded that the Inter Integrated Circuit (I2C) data bus, as implemented in a great majority of the CubeSats, caused some catastrophic satellite failures and a vast amount of bus lockups. The power distribution may lead to catastrophic failures if the power lines are not protected against overcurrent. A connector and wiring standard widely implemented in CubeSats is based on the PC/104 standard. Most participants find the 104 pin connector of this standard too large. For a future CubeSat bus interface standard, it is recommended to implement a reliable data bus, a power distribution with overcurrent protection and a wiring harness with smaller connectors compared with PC/104.