Computer Science – Performance
Scientific paper
Sep 2003
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2003esasp.524..423d&link_type=abstract
In: Proceedings of the 10th European Space Mechanisms and Tribology Symposium, 24-26 September 2003, San Sebastián, Spain. Compi
Computer Science
Performance
Equipment Mechanisms
Scientific paper
During the launching phase, satellites are undoubtedly faced to severe mechanical environment, which appears to be one of the most critical issues to cope with. Various solutions can be investigated to protect the onboard equipments during these critical phases. Actually, theses vibratory damages can be reduced at the same time by optimising the architecture of the satellite but also by local actions aiming more on the propagation of the vibrations and thus limiting the transmission of the vibrations through the whole equipment. The latter solution also called "passive solution" is developed by SMAC under the CNES contract to protect along all six degree of freedom the small reaction wheel, chosen for the MYRIADE microsatellite family, from random vibrations and shocks. This original solution consists in uncoupling the reaction wheel from the satellite structure by an isolator system made out of a high damping viscoelastic material: the SMACTANE®. Technical trade-off and design issue, that has led to select the final flight configuration, will be discussed in parallel with the design constraints in term of: mass and size, due to the lack of space onboard MYRIADE platform, and transfer function performances, addressing low cut-off frequency and quality-factor limitation at cut-off frequency. In particular, the solution implemented in order to minimize coupling phenomenon between axis will be particularly described. Main features of the flight models and the qualification tests results will be given. Despite many advantages, it is well known that damping viscoelastic materials have some disadvantages, like their non-linear behaviour depending on the mechanical levels applied and their poor thermal and electric conductivity. So, to conclude, we try to show how new ways seem to be promising and keep all interest in using viscoelastic materials in space applications. On the one hand, the way to specify the damping performances and to characterize them will be in particular discussed. On the other hand, an alternative solution to the thermal braids here selected is currently investigated under CNES R&T funding to avoid additional parts and also parasitic stiffness in parallel of the elastomer mounts. The first tests results of a new kind of elastomeric material developed will also be addressed.
Demerville T.
Guay Ph.
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