Modular structure for small satellites

Details Modular structure for small satellites Modular structure for small satellites

Nov 2004

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2004esasp.571e..53m&link_type=abstract

Proceedings of The 4S Symposium: Small Satellites, Systems and Services (ESA SP-571). 20 - 24 September 2004, La Rochelle, Franc

Physics

Scientific paper

The main objective of this work was to design and characterize concepts for structures of small satellites. Low cost solutions, short development cycles, structural concepts allowing maximum freedom in payload accommodation, and structure applicability for several launchers were the key principles that were followed. In this study an extensive approach was made to modularity in spacecraft structures. A wide collection of existing spacecraft was analyzed and the commonalties were identified. A selection of common elements was made and design rules were developed. Furthermore a real spacecraft (a breadboard model) was designed and built out of these common elements. Finally the feasibility of the common elements was demonstrated in sine vibration test.

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