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dc.contributor.supervisor Telichev, Igor (Mechanical Engineering) en_US
dc.contributor.author Jones, Alexander James Bryan
dc.date.accessioned 2018-02-05T22:17:49Z
dc.date.available 2018-02-05T22:17:49Z
dc.date.issued 2018
dc.identifier.uri http://hdl.handle.net/1993/32882
dc.description.abstract Many commonly-used orbits are increasingly cluttered with orbital debris, posing a significant threat to space assets, which require enhanced protection. Recent studies demonstrate that foam-core structural and orbital debris protection panels are a promising alternative to single-function shields. The objective of this thesis was to develop a two-dimensional model capable of simulating orbital debris impacts with foam-core panels cheaply and quickly, for initial shielding evaluation. The selected strategy combines explicit time integration, SPH, and FE methods, found by comparison of numerical and physical experiments. It was found that the Johnson-Cook strength and failure equations, with the Mie-Gruneisen equation of state provide the best fit with selected test data. It was suggested that the multi-shock effect of open-cell foam ligaments could be replicated using a multi-layered structure of equivalent mass. The developed model predicted the outcome of all simulated NASA tests while completing the numerical analysis significantly faster than three-dimensional models. en_US
dc.subject Orbital debris en_US
dc.subject Numerical modelling en_US
dc.subject Metal foam core en_US
dc.subject Hypervelocity impact en_US
dc.subject Autodyn en_US
dc.subject MMOD en_US
dc.subject HVI en_US
dc.title Modelling of hypervelocity impact on foam-core sandwich panel with enhanced capability for orbital debris protection en_US
dc.degree.discipline Mechanical Engineering en_US
dc.contributor.examiningcommittee Wu, Nan (Mechanical Engineering) Cha, Young-Jin (Civil Engineering) en_US
dc.degree.level Master of Science (M.Sc.) en_US
dc.description.note May 2018 en_US


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