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- W4386111811 abstract "Abstract. Shock loads are very high amplitude and short duration transient loads. They are produced in space structures by pyrotechnic devices placed in the launchers initiating the stage or fairing separations. While the spacecraft structure is not susceptible to this range of frequencies, electrical units could be seriously damaged during the launch phase. Shock tests are performed on the electrical units to verify if they withstand the transient loads, thus their compliance to the requirements. To understand how the input force evolves from the launcher-spacecraft interface to the equipment of interest, a model of the dynamical behaviour of the spacecraft at high frequencies has to be developed. An initial approach constitutes the implementation of a mathematical model through the use of Statistical Energy Analysis (SEA). The results of a 4 degrees of freedom model using SEA will be shown. The model can be further developed by the integration of data-driven techniques. In this work a description of two different approaches is presented, that include model-based and data-driven methods. Finally, a cross-cutting potential solution is briefly introduced; it will combine experimental data with a mathematical model as to convey them in the training database of an Artificial Neural Network algorithm. The hybrid solution will possibly turn out as a reliable and efficient way to break down time and costs of the shock test campaign." @default.
- W4386111811 created "2023-08-24" @default.
- W4386111811 creator A5010435599 @default.
- W4386111811 date "2023-09-01" @default.
- W4386111811 modified "2023-09-26" @default.
- W4386111811 title "Comparison of predictive techniques for spacecraft shock environment" @default.
- W4386111811 doi "https://doi.org/10.21741/9781644902677-24" @default.
- W4386111811 hasPublicationYear "2023" @default.
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