Robust and Scalable Electronic Power System for Small Satellites

Paper number

IAC-12,B4,7A,3,x14718

Author

Mr. Stefano Speretta, ISIS - Innovative Solutions In Space B.V., The Netherlands

Coauthor

Mr. Chetan Angadi, Stanford University & Delft University of Technology (TU Delft), The Netherlands

Coauthor

Mr. Joost Elstak, ISIS - Innovative Solutions In Space B.V., The Netherlands

Coauthor

Dr. Bert Monna, Systematic, The Netherlands

Coauthor

Mr. Frank Stelwagen, Systematic, The Netherlands

Year

2012

Abstract

Advances in contemporary space mission design allow for the development of more and more miniaturized spacecrafts with a short development time. Most of the attention in the previous years was focused on small satellites around 1-5 kg, while now many missions are shifting towards 10-50 kg satellites. To support the two markets, ISIS - Innovative Solutions In Space B.V. and SystematIC design B.V. jointly started the development of a versatile and scalable power system. Since Electronic Power Systems are crucial in satellites and are reported as one of the main causes for failure in several small satellite missions, reliability has always been the most important goal of the design. 

This paper presents the newly designed EPS and the design and testing methodologies followed. EPS has been developed with COTS components leading to cost effective mass production. Yet the system is qualified for space flight in LEO. Particular attention was paid to avoid Single Point Failures and to have a redundant system capable of tolerating faults. To properly address such a wide market a scalable design was selected, allowing fitting the system for 2U CubeSats with only body mounted cells up to 12U CubeSats with deployable panels. If a higher redundancy level is required, the power system can be connected in a hot / cold redundant setup. This solution also allows further widening the application range to 20 – 50 kg satellites.

Battery technology was also carefully evaluated to achieve the previously mentioned performance and characterization procedures and results have been elaborated according to ECSS standards. Extensive characterization is being performed to achieve confidence on the battery lifetime estimation. Suitable thermal design has also been carried out to ensure safe operation of batteries at an optimal temperature.

The development of this new line of products takes advantage of the synergy between the partners, with different backgrounds but all focused to improve the performance of current space systems to fit highly demanding small satellite missions.

Abstract document

IAC-12,B4,7A,3,x14718.brief.pdf

Manuscript document

IAC-12,B4,7A,3,x14718.pdf (🔒 authorized access only).

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