Modal survey test and model correlation of the CASSIOPE spacecraft

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Proceedings titleConference Proceedings of the Society for Experimental Mechanics Series
Conference28th IMAC, A Conference on Structural Dynamics, 2010, 1 February 2010 through 4 February 2010, Jacksonville, FL
IssuePART 2
Pages11371145; # of pages: 9
SubjectCoupled loads analysis; Electronics box; Environmental loads; Experimental data; Experimental modal analysis; Finite element models; Flight models; Frequency domains; Iterative update; Measured data; Mechanical vibrations; Modal parameters; Modal survey tests; Modal test; Model correlation; Multi-input multi-output; Multichannel data; Multiple inputs; Qualification test; Spacecraft design; Time-domain data; Accelerometers; Automobile electronic equipment; Coupled circuits; Dynamics; Finite element method; Forecasting; Launch vehicles; Launching; MIMO systems; Structural analysis; Structural dynamics; Surveys; Testing; Time domain analysis; Vibration analysis; Modal analysis
AbstractA comprehensive modal survey test based on multi-input multi-output experimental modal analysis techniques was conducted on the CASSIOPE spacecraft. This paper describes the details of the methodology used to perform the successful experimental modal test to efficiently extract the critical modes of the spacecraft. Results from the modal test have been used to validate the analytical finite element model and to provide confidence in the structural integrity of the spacecraft design. The test was performed on the flight model of the CASSIOPE spacecraft in the final stages of integration, which included all of the payload and bus instruments and electronics boxes. The multiple-input excitation for the spacecraft was generated using two portable electrodynamic modal shakers installed on the top and bottom of the spacecraft to distribute the excitation energy and the response was measured using 81 miniature accelerometers. A digital multi-channel data acquisition system was used to record the time domain data and calculate the frequency domain spectra. Advanced modal analysis software was used to extract modal parameters from the measured data and critical modes were compared with predictions from the finite element model. Most modes identified through the experimental data compared favorably with the predictions. Nevertheless, some differences were large enough to require iterative update of the finite elelement model. The structural dynamics information from the updated finite element model was used to plan the mechanical vibration qualification test and predict the response of the spacecraft to the launch vehicle environmental loads through coupled loads analysis. ©2010 Society for Experimental Mechanics Inc.
Publication date
AffiliationNational Research Council Canada (NRC-CNRC); Aerospace (AERO-AERO)
Peer reviewedYes
NPARC number21271508
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Record identifier6c4b8d60-8c42-4e4e-80a7-acac560145a7
Record created2014-03-24
Record modified2016-05-09
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