Design and Validation of a Flexible Spacecraft Model for Attitude Control Applications
Gianluca Tagliani
Design and Validation of a Flexible Spacecraft Model for Attitude Control Applications.
Rel. Elisa Capello, Mauro Mancini. Politecnico di Torino, Corso di laurea magistrale in Ingegneria Aerospaziale, 2022
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Abstract
The purpose of this thesis is the assessment of a comparison between a flexible spacecraft model, studied during previous theses and scientific articles, and the implementation of the same spacecraft in the software MSC Adams, aiming at validating the model. Thanks to this innovative tool it is possible to evaluate several features the user could desire to have available, conducting a non-linear multi-body analysis, that allows to provide more realistic data sets. The Picard satellite of the French Space Agency (CNES) is used as the main body of the spacecraft and its dynamics is expressed with Euler equations for a rigid body.
The configuration, in terms of locations and dimensions, of the solar panels and the reaction wheels has been modified with respect to Picard in order to have advantages during the construction of the spacecraft in MSC Adams and to have a more general type of satellite
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