Abstract
Non-linear elements are present in practically all spacecraft structures. The assumption of a (quasi-)linear structure is nevertheless adequate for structural analyses and design verification purposes in those cases where these structural non-linearities are relatively weak or not substantially activated by the mechanical environments encountered during the launch or during ground testing. However, when significant non-linear effects in spacecraft structures are no longer negligible then linear modal analysis will not be able to handle non-linear dynamical phenomena in an adequate manner: the development of a non-linear analogue of linear modal analysis becomes an urgent and important issue. The objective of this paper is to show that nonlinear normal modes (NNMs) represent a useful and practical tool in this context. A full-scale spacecraft structure is considered and is modeled using the finite element method. Its NNMs are computed using advanced numerical algorithms, and the resulting dynamics is then carefully analyzed. Nonlinear phenomena with no linear counterpart including nonlinear modal interactions are also highlighted.
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Acknowledgements
This paper has been prepared in the framework of the ESA Technology Research Programme study “Advancement of Mechanical Verification Methods for Non-linear Spacecraft Structures (NOLISS)” (ESA contract No.21359/08/NL/SFe).
The authors would like to thank Dr. Maxime Peeters for all the constructive discussions. The author L. Renson would like to acknowledge the Belgian National Fund for Scientific Research (FRIA fellowship) for its financial support.
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© 2012 The Society for Experimental Mechanics, Inc. 2012
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Renson, L., Kerschen, G., Newerla, A. (2012). Nonlinear Modal Analysis of the Smallsat Spacecraft. In: Adams, D., Kerschen, G., Carrella, A. (eds) Topics in Nonlinear Dynamics, Volume 3. Conference Proceedings of the Society for Experimental Mechanics Series. Springer, New York, NY. https://doi.org/10.1007/978-1-4614-2416-1_5
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DOI: https://doi.org/10.1007/978-1-4614-2416-1_5
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