DEVELOPMENT OF A THERMAL DESIGN MODEL FOR A SMALL SPACECRAFT WITH AN INTEGRATED HEAT PIPE

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dc.contributor.authorYensebayeva, Madina
dc.date.accessioned2022-06-30T10:03:28Z
dc.date.available2022-06-30T10:03:28Z
dc.date.issued2022-04
dc.description.abstractThermal management is essential to ensure maximum performance and mission success. The temperature conditions apply to each payload component and to the spacecraft as a whole. These specifications may include a range of operating temperatures, exceeding which may lead to deterioration or irreversible damage to a part of the satellite. Heat pipes are very useful for cooling satellites and temperature stabilization due to their lighter weight, low maintenance, and high durability. The aim of the research is to achieve a deeper comprehension of the heat pipe thermodynamic processes and design new satellite heat transfer network. For this goal, a lumped parameter model for network of heat pipes has been developed with the finite element model to conduct a combined thermal assessment and address significant technical difficulties, such as spacecraft cooling. The proposed model can be improved and used as an effective heat transfer system of the satellite in the future. Keywords: heat pipe, lumped parameter model, heat transfer, satellite, thermal equilibriumen_US
dc.identifier.citationYensebayeva, M. (2022). DEVELOPMENT OF A THERMAL DESIGN MODEL FOR A SMALL SPACECRAFT WITH AN INTEGRATED HEAT PIPE (Unpublished master's thesis). Nazarbayev University, Nur-Sultan, Kazakhstanen_US
dc.identifier.urihttp://nur.nu.edu.kz/handle/123456789/6356
dc.language.isoenen_US
dc.publisherNazarbayev University School of Engineering and Digital Sciencesen_US
dc.rightsAttribution-NonCommercial-ShareAlike 3.0 United States*
dc.rights.urihttp://creativecommons.org/licenses/by-nc-sa/3.0/us/*
dc.subjectheat pipeen_US
dc.subjectType of access: Open Accessen_US
dc.subjectResearch Subject Categories::TECHNOLOGYen_US
dc.subjectlumped parameter modelen_US
dc.subjectheat transferen_US
dc.subjectsatelliteen_US
dc.subjectthermal equilibriumen_US
dc.titleDEVELOPMENT OF A THERMAL DESIGN MODEL FOR A SMALL SPACECRAFT WITH AN INTEGRATED HEAT PIPEen_US
dc.typeMaster's thesisen_US
workflow.import.sourcescience

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