{"id":{"repo_id":"mit","oai_identifier":"oai:dspace.mit.edu:1721.1/105622"},"canonical_url":"https://search.dev.ndltd.org/etd/mit/oai:dspace.mit.edu:1721.1/105622","repository":{"repo_id":"mit","name":"MIT","base_url":"https://dspace.mit.edu/oai/request"},"display":{"title":"Application of Bayesian-based uncertainty and global sensitivity analyses to spacecraft thermal design","abstract":"As satellite design has increased in complexity, the evolution of thermal engineering of spacecraft has plateaued. For years, thermal engineers have used the same principles of designing to stacked worst case scenarios and applying additional margin on top of the already conservative predictions. Recent publications have proposed the use of Bayesian-based propabilistic tools in the design of spacecraft in the effort to avoid overly conservative thermal designs. An issue with utilizing these tools is the typically high computational cost associated with traditional thermal modeling. To help bridge the gap from state-of-the-art to industry standard, this thesis develops a methodology to reduce simulation time and implement these analysis techniques in the industry standard software, Cullimore & Ring Technologies Inc., Thermal Desktop. These design methods are applied to the REgolith X-ray Imaging Spectrometer (REXIS), a student built x-ray spectrometer aboard NASA's OSIRIS-REx mission. Uncertainty analysis shows the area of the main instrument's radiator could have been reduced by 11%, as compared to the design obtained from conventional techniques, and still have a 99% probability of meeting the thermal requirements in all mission phases. Furthermore, global sensitivity analysis results provide insight into the thermal design of the instrument which could have been used to avoid anomalies experienced during integration and testing. Overall, results show that previously established analysis techniques scale to more complex thermal systems and the insights gained from these methodologies can significantly reduce thermal overdesign.","abstract_html":"As satellite design has increased in complexity, the evolution of thermal engineering of spacecraft has plateaued. For years, thermal engineers have used the same principles of designing to stacked worst case scenarios and applying additional margin on top of the already conservative predictions. Recent publications have proposed the use of Bayesian-based propabilistic tools in the design of spacecraft in the effort to avoid overly conservative thermal designs. An issue with utilizing these tools is the typically high computational cost associated with traditional thermal modeling. To help bridge the gap from state-of-the-art to industry standard, this thesis develops a methodology to reduce simulation time and implement these analysis techniques in the industry standard software, Cullimore & Ring Technologies Inc., Thermal Desktop. These design methods are applied to the REgolith X-ray Imaging Spectrometer (REXIS), a student built x-ray spectrometer aboard NASA's OSIRIS-REx mission. Uncertainty analysis shows the area of the main instrument's radiator could have been reduced by 11%, as compared to the design obtained from conventional techniques, and still have a 99% probability of meeting the thermal requirements in all mission phases. Furthermore, global sensitivity analysis results provide insight into the thermal design of the instrument which could have been used to avoid anomalies experienced during integration and testing. Overall, results show that previously established analysis techniques scale to more complex thermal systems and the insights gained from these methodologies can significantly reduce thermal overdesign.","abstract_has_math":false,"creators":["McMenamin, Conor B. (Conor Brendan)"],"institution":"Massachusetts Institute of Technology","degree_name":null,"degree_level":null,"degree_discipline":null,"degree_department":"Massachusetts Institute of Technology. Department of Aeronautics and Astronautics.","school":null,"contributors":[],"advisors":["Rebecca A. Masterson and Richard P. Binzel."],"committee_chairs":[],"committee_members":[],"year":2016,"date_issued":"2016","date_published":"2016","updated_at":"2026-07-22T22:21:26Z","subjects":["Aeronautics and Astronautics."],"languages":["eng"],"rights":["M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. 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