{"id":{"repo_id":"uiuc","oai_identifier":"oai:www.ideals.illinois.edu:2142/124396"},"canonical_url":"https://search.dev.ndltd.org/etd/uiuc/oai:www.ideals.illinois.edu:2142/124396","repository":{"repo_id":"uiuc","name":"University of Illinois - Urbana-Champaign","base_url":"https://www.ideals.illinois.edu/oai-pmh"},"display":{"title":"A real time thermal simulator for small spacecraft in an orbital environment","abstract":"Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2024-09-16 without embargo terms","abstract_html":"Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2024-09-16 without embargo terms","abstract_has_math":false,"creators":["Lim, Qi"],"institution":"University of Illinois at Urbana-Champaign","degree_name":"M.S.","degree_level":"Thesis","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":["Lembeck, Michael F"],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2024,"date_issued":"2024-05","date_published":"2024-05","updated_at":"2026-07-22T22:25:00Z","subjects":["Thermal Analysis","Small Spacecraft"],"languages":["en","eng"],"rights":["Copyright 2024 Qi Lim"],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"https://hdl.handle.net/2142/124396","outbound_label":"Handle","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Lembeck, Michael F"]},{"key":"dc:creator","label":"Author","values":["Lim, Qi"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2024-05","2024-04-30"]},{"key":"dc:type","label":"Dc Type","values":["text"]},{"key":"thesis:degree_discipline","label":"Discipline","values":["Aerospace Engineering"]},{"key":"thesis:degree_level","label":"Degree Level","values":["Thesis"]},{"key":"thesis:degree_name","label":"Degree Name","values":["M.S."]},{"key":"thesis:institution_name","label":"Thesis Institution Name","values":["University of Illinois at Urbana-Champaign"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["Thermal Analysis","Small Spacecraft"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language","label":"Dc Language","values":["en","eng"]},{"key":"dc:rights","label":"Dc Rights","values":["Copyright 2024 Qi Lim"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["https://hdl.handle.net/2142/124396"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description","label":"Description","values":["Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2024-09-16 without embargo terms","The student, Qi Lim, accepted the attached license on 2024-04-24 at 14:29.","The student, Qi Lim, submitted this Thesis for approval on 2024-04-24 at 14:32.","This Thesis was approved for publication on 2024-04-30 at 10:22.","DSpace SAF Submission Ingestion Package generated from Vireo submission #20617 on 2024-09-16 at 00:36:55","This thesis presents a thermal solver for small spacecraft written in MATLAB that interfaces with a.i. Solutions’ FreeFlyer mission design software. Thermal control on small spacecraft is a dynamic challenge, influenced by the ever-changing environment. Heat is sourced from both within and outside the spacecraft. Powered components impose heat loads, radiating and conducting energy into their surroundings. The sun and other celestial bodies contribute a varying flux upon the exterior of the spacecraft depending on the spacecraft’s relative position. The thermal solver takes all these factors into account, simulating the spacecraft’s environment, and produces interpretable results for analysis. Thermal analysis examines potential temperature gradients inside a spacecraft. The thermal solver written for this thesis is a user-friendly tool for space systems design tasks. Integrating this solver with an industry-level orbital propagator can improve the fidelity of thermal analysis beyond that commercial-grade software packages typically provide. Where standalone analysis software sometimes presents a cumbersome user experience for setting up an orbital environment, this solver solves the issue by interfacing with an external propagator, a.i. Solutions’ FreeFlyerTM. This allows for the setup of complex missions that may involve orbital maneuvers and changes in spacecraft attitude, providing an integrated analysis mission model. Verification of the thermal solver was demonstrated by correlating results with the available Siemens Simcenter 3D commercial software. Future improvements to the user interface are possible, but the basic solver is now ready for use in analyzing Laboratory for Advanced Space Systems at Illinois (LASSI) missions."]},{"key":"dc:format","label":"Dc Format","values":["application/pdf"]},{"key":"dc:title","label":"Title","values":["A real time thermal simulator for small spacecraft in an orbital environment"]}]}],"canonical_facts":{"dc:contributor":["Lembeck, Michael F"],"dc:creator":["Lim, Qi"],"dc:date":["2024-05","2024-04-30"],"dc:description":["Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2024-09-16 without embargo terms","The student, Qi Lim, accepted the attached license on 2024-04-24 at 14:29.","The student, Qi Lim, submitted this Thesis for approval on 2024-04-24 at 14:32.","This Thesis was approved for publication on 2024-04-30 at 10:22.","DSpace SAF Submission Ingestion Package generated from Vireo submission #20617 on 2024-09-16 at 00:36:55","This thesis presents a thermal solver for small spacecraft written in MATLAB that interfaces with a.i. Solutions’ FreeFlyer mission design software. Thermal control on small spacecraft is a dynamic challenge, influenced by the ever-changing environment. Heat is sourced from both within and outside the spacecraft. Powered components impose heat loads, radiating and conducting energy into their surroundings. The sun and other celestial bodies contribute a varying flux upon the exterior of the spacecraft depending on the spacecraft’s relative position. The thermal solver takes all these factors into account, simulating the spacecraft’s environment, and produces interpretable results for analysis. Thermal analysis examines potential temperature gradients inside a spacecraft. The thermal solver written for this thesis is a user-friendly tool for space systems design tasks. Integrating this solver with an industry-level orbital propagator can improve the fidelity of thermal analysis beyond that commercial-grade software packages typically provide. Where standalone analysis software sometimes presents a cumbersome user experience for setting up an orbital environment, this solver solves the issue by interfacing with an external propagator, a.i. Solutions’ FreeFlyerTM. This allows for the setup of complex missions that may involve orbital maneuvers and changes in spacecraft attitude, providing an integrated analysis mission model. Verification of the thermal solver was demonstrated by correlating results with the available Siemens Simcenter 3D commercial software. Future improvements to the user interface are possible, but the basic solver is now ready for use in analyzing Laboratory for Advanced Space Systems at Illinois (LASSI) missions."],"dc:format":["application/pdf"],"dc:identifier":["https://hdl.handle.net/2142/124396"],"dc:language":["en","eng"],"dc:rights":["Copyright 2024 Qi Lim"],"dc:subject":["Thermal Analysis","Small Spacecraft"],"dc:title":["A real time thermal simulator for small spacecraft in an orbital environment"],"dc:type":["text"],"thesis:degree_discipline":["Aerospace Engineering"],"thesis:degree_level":["Thesis"],"thesis:degree_name":["M.S."],"thesis:institution_name":["University of Illinois at Urbana-Champaign"]},"updated_at":"2026-07-22T22:25:00Z"}