In this paper a method capable of the identification of non-linear structures with many degrees of freedom is presented. The Non-Linear Resonant Decay Method achieves this by identifying an underlying linear modal model for the system. Force appropriation is then used to apply sinusoidal bursts to the structure at high levels of force. The system responses to these bursts are used in a regression analysis in modal space to yield a limited number of additional non-linear terms. The method is applied to a simulated continuous system representing a wing/engine structure with discrete non-linear components at the engine attachment points. The resulting identified non-linear modal model is used to generate response data which are compared with responses from the original system.
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ASME 7th Biennial Conference on Engineering Systems Design and Analysis
July 19–22, 2004
Manchester, England
ISBN:
0-7918-4174-X
PROCEEDINGS PAPER
Identification of a Simulated Continuous Structure With Discrete Non-Linear Components Using an Extended Modal Model
Michael F. Platten
,
Michael F. Platten
University of Manchester, Manchester, UK
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Jan R. Wright
,
Jan R. Wright
University of Manchester, Manchester, UK
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Jonathan E. Cooper
Jonathan E. Cooper
University of Manchester, Manchester, UK
Search for other works by this author on:
Michael F. Platten
University of Manchester, Manchester, UK
Jan R. Wright
University of Manchester, Manchester, UK
Jonathan E. Cooper
University of Manchester, Manchester, UK
Paper No:
ESDA2004-58496, pp. 229-236; 8 pages
Published Online:
November 11, 2008
Citation
Platten, MF, Wright, JR, & Cooper, JE. "Identification of a Simulated Continuous Structure With Discrete Non-Linear Components Using an Extended Modal Model." Proceedings of the ASME 7th Biennial Conference on Engineering Systems Design and Analysis. Volume 2. Manchester, England. July 19–22, 2004. pp. 229-236. ASME. https://doi.org/10.1115/ESDA2004-58496
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