{"id":{"repo_id":"uiuc","oai_identifier":"oai:www.ideals.illinois.edu:2142/120427"},"canonical_url":"https://search.dev.ndltd.org/etd/uiuc/oai:www.ideals.illinois.edu:2142/120427","repository":{"repo_id":"uiuc","name":"University of Illinois - Urbana-Champaign","base_url":"https://www.ideals.illinois.edu/oai-pmh"},"display":{"title":"Robust trajectory and guidance optimization for guided powered descent and landing","abstract":"Submission published under a 24 month embargo labeled 'U of I Access', the embargo will last until 2025-05-01","abstract_html":"Submission published under a 24 month embargo labeled 'U of I Access', the embargo will last until 2025-05-01","abstract_has_math":false,"creators":["Calkins, Grace Elizabeth"],"institution":"University of Illinois at Urbana-Champaign","degree_name":"M.S.","degree_level":"Thesis","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":["Putnam, Zachary R"],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2023,"date_issued":"2023-05","date_published":"2023-05","updated_at":"2026-07-22T22:24:57Z","subjects":["Trajectory Optimization","Gnc","Edl","Aerospace","Safe And Precise Landing","Navigation"],"languages":["en","eng"],"rights":["Copyright 2023 Grace Calkins"],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"https://hdl.handle.net/2142/120427","outbound_label":"Handle","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Putnam, Zachary R"]},{"key":"dc:creator","label":"Author","values":["Calkins, Grace Elizabeth"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2023-05","2023-05-01"]},{"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":["Trajectory Optimization","Gnc","Edl","Aerospace","Safe And Precise Landing","Navigation"]}]},{"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 Grace Calkins"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["https://hdl.handle.net/2142/120427"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description","label":"Description","values":["Submission published under a 24 month embargo labeled 'U of I Access', the embargo will last until 2025-05-01","The student, Grace Calkins, accepted the attached license on 2023-04-26 at 14:21.","The student, Grace Calkins, submitted this Thesis for approval on 2023-04-26 at 14:26.","This Thesis was approved for publication on 2023-05-01 at 14:47.","DSpace SAF Submission Ingestion Package generated from Vireo submission #19196 on 2023-09-01 at 17:15:06","A robust trajectory optimization approach for guidance algorithm gain and target vector selection for powered descent and landing is developed. A genetic algorithm is used to determine optimal guidance algorithm parameters that minimize the impact of environment, navigation, vehicle property uncertainty. Vehicle state uncertainties are computed rapidly using linear covariance analysis techniques. When implemented in the guidance algorithm, the optimal gains and target vectors shape a trajectory that has more favorable conditions for a given navigation sensor suite. As a demonstration of this method, the optimal guidance parameters are found for a multi-phase trajectory from powered descent initiation to touchdown for a robotic lunar landing mission. Optimal guidance parameters are found for different optimization variable sets, sensor suite compositions and qualities, and with objective functions to minimize variability in propellant usage or terminal position. Multi-objective optimization showing the tradeoff between terminal position uncertainty and total propellant usage is presented for varying sensor suite fidelities and sensor suite compositions. Results show that the optimal guidance algorithm parameters for a given trajectory differ based on the sensor suite and result in performance improvements over the baseline in propellant usage and terminal accuracy. Improvements of up to a 20% reduction in landed footprint size and up to a 5% reduction in total propellant usage can be seen when using robust trajectory optimization, and operating with a lower quality sensor suite becomes viable when optimal guidance parameters are used."]},{"key":"dc:format","label":"Dc Format","values":["application/pdf"]},{"key":"dc:title","label":"Title","values":["Robust trajectory and guidance optimization for guided powered descent and landing"]}]}],"canonical_facts":{"dc:contributor":["Putnam, Zachary R"],"dc:creator":["Calkins, Grace Elizabeth"],"dc:date":["2023-05","2023-05-01"],"dc:description":["Submission published under a 24 month embargo labeled 'U of I Access', the embargo will last until 2025-05-01","The student, Grace Calkins, accepted the attached license on 2023-04-26 at 14:21.","The student, Grace Calkins, submitted this Thesis for approval on 2023-04-26 at 14:26.","This Thesis was approved for publication on 2023-05-01 at 14:47.","DSpace SAF Submission Ingestion Package generated from Vireo submission #19196 on 2023-09-01 at 17:15:06","A robust trajectory optimization approach for guidance algorithm gain and target vector selection for powered descent and landing is developed. A genetic algorithm is used to determine optimal guidance algorithm parameters that minimize the impact of environment, navigation, vehicle property uncertainty. Vehicle state uncertainties are computed rapidly using linear covariance analysis techniques. When implemented in the guidance algorithm, the optimal gains and target vectors shape a trajectory that has more favorable conditions for a given navigation sensor suite. As a demonstration of this method, the optimal guidance parameters are found for a multi-phase trajectory from powered descent initiation to touchdown for a robotic lunar landing mission. Optimal guidance parameters are found for different optimization variable sets, sensor suite compositions and qualities, and with objective functions to minimize variability in propellant usage or terminal position. Multi-objective optimization showing the tradeoff between terminal position uncertainty and total propellant usage is presented for varying sensor suite fidelities and sensor suite compositions. Results show that the optimal guidance algorithm parameters for a given trajectory differ based on the sensor suite and result in performance improvements over the baseline in propellant usage and terminal accuracy. Improvements of up to a 20% reduction in landed footprint size and up to a 5% reduction in total propellant usage can be seen when using robust trajectory optimization, and operating with a lower quality sensor suite becomes viable when optimal guidance parameters are used."],"dc:format":["application/pdf"],"dc:identifier":["https://hdl.handle.net/2142/120427"],"dc:language":["en","eng"],"dc:rights":["Copyright 2023 Grace Calkins"],"dc:subject":["Trajectory Optimization","Gnc","Edl","Aerospace","Safe And Precise Landing","Navigation"],"dc:title":["Robust trajectory and guidance optimization for guided powered descent and landing"],"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":"2026-07-22T22:24:57Z"}