{"id":{"repo_id":"uiuc","oai_identifier":"oai:www.ideals.illinois.edu:2142/122076"},"canonical_url":"https://search.dev.ndltd.org/etd/uiuc/oai:www.ideals.illinois.edu:2142/122076","repository":{"repo_id":"uiuc","name":"University of Illinois - Urbana-Champaign","base_url":"https://www.ideals.illinois.edu/oai-pmh"},"display":{"title":"Designing low thrust missions in cislunar space","abstract":"Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2024-03-01 without embargo terms","abstract_html":"Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2024-03-01 without embargo terms","abstract_has_math":false,"creators":["Fofrich, Joshua"],"institution":"University of Illinois at Urbana-Champaign","degree_name":"M.S.","degree_level":"Thesis","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":["Woollands, Robyn M"],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2023,"date_issued":"2023-12","date_published":"2023-12","updated_at":"2026-07-22T22:25:00Z","subjects":["Low Thrust Trajectory Optimization","Adaptive Picard Chebyshev","Chebyshev"],"languages":["en","eng"],"rights":["Copyright 2023 Joshua Fofrich"],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"https://hdl.handle.net/2142/122076","outbound_label":"Handle","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Woollands, Robyn M"]},{"key":"dc:creator","label":"Author","values":["Fofrich, Joshua"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2023-12","2023-12-08"]},{"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":["Low Thrust Trajectory Optimization","Adaptive Picard Chebyshev","Chebyshev"]}]},{"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 2023 Joshua Fofrich"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["https://hdl.handle.net/2142/122076"]}]},{"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 2024-03-01 without embargo terms","The student, Joshua Fofrich, accepted the attached license on 2023-12-08 at 08:42.","The student, Joshua Fofrich, submitted this Thesis for approval on 2023-12-08 at 08:50.","This Thesis was approved for publication on 2023-12-08 at 09:39.","DSpace SAF Submission Ingestion Package generated from Vireo submission #20179 on 2024-03-01 at 13:15:31","This thesis describes the methodology and results that were obtained for computing a low-thrust, minimumfuel, trajectory from a highly eccentric Near Rectilinear Halo Orbit (NRHO) in the Earth-Moon system to a highly inclined, circular, low lunar orbit (LLO). The trajectory optimization is formulated using an indirect optimization method, and the Modified Equinoctial Elements are used as the coordinates of choice. The MEEs, with five slow variables, are well-suited to solving two-point boundary value problems over long time intervals. The simulated dynamics include a 3×3 gravity model for the Moon, third-body perturbations from the Earth and Sun, and a solar radiation pressure model. We show a candidate transfer trajectory solution that reaches the LLO with an altitude of 100 km, from the Near Rectilinear Halo Orbit. Furthermore, this thesis describes the methodology and results that were obtained for performing orbit determination of a lunar orbiting spacecraft using high fidelity dynamics. Simulated dynamics for the orbit determination portion of the thesis include a 60 × 60 lunar gravity model, third body perturbations from the Earth and Sun, and solar radiation pressure. A batch least squares estimator was used for the analysis with Earth based observations. The adaptive Picard-Chebyshev integrator is used throughout this thesis and is shown to be an order of magnitude faster than traditional integration algorithms such as ODE113 and ODE45."]},{"key":"dc:format","label":"Dc Format","values":["application/pdf"]},{"key":"dc:title","label":"Title","values":["Designing low thrust missions in cislunar space"]}]}],"canonical_facts":{"dc:contributor":["Woollands, Robyn M"],"dc:creator":["Fofrich, Joshua"],"dc:date":["2023-12","2023-12-08"],"dc:description":["Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2024-03-01 without embargo terms","The student, Joshua Fofrich, accepted the attached license on 2023-12-08 at 08:42.","The student, Joshua Fofrich, submitted this Thesis for approval on 2023-12-08 at 08:50.","This Thesis was approved for publication on 2023-12-08 at 09:39.","DSpace SAF Submission Ingestion Package generated from Vireo submission #20179 on 2024-03-01 at 13:15:31","This thesis describes the methodology and results that were obtained for computing a low-thrust, minimumfuel, trajectory from a highly eccentric Near Rectilinear Halo Orbit (NRHO) in the Earth-Moon system to a highly inclined, circular, low lunar orbit (LLO). The trajectory optimization is formulated using an indirect optimization method, and the Modified Equinoctial Elements are used as the coordinates of choice. The MEEs, with five slow variables, are well-suited to solving two-point boundary value problems over long time intervals. The simulated dynamics include a 3×3 gravity model for the Moon, third-body perturbations from the Earth and Sun, and a solar radiation pressure model. We show a candidate transfer trajectory solution that reaches the LLO with an altitude of 100 km, from the Near Rectilinear Halo Orbit. Furthermore, this thesis describes the methodology and results that were obtained for performing orbit determination of a lunar orbiting spacecraft using high fidelity dynamics. Simulated dynamics for the orbit determination portion of the thesis include a 60 × 60 lunar gravity model, third body perturbations from the Earth and Sun, and solar radiation pressure. A batch least squares estimator was used for the analysis with Earth based observations. The adaptive Picard-Chebyshev integrator is used throughout this thesis and is shown to be an order of magnitude faster than traditional integration algorithms such as ODE113 and ODE45."],"dc:format":["application/pdf"],"dc:identifier":["https://hdl.handle.net/2142/122076"],"dc:language":["en","eng"],"dc:rights":["Copyright 2023 Joshua Fofrich"],"dc:subject":["Low Thrust Trajectory Optimization","Adaptive Picard Chebyshev","Chebyshev"],"dc:title":["Designing low thrust missions in cislunar space"],"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"}