Evaluation of an optimal aerocapture guidance algorithm for human Mars missions

dc.contributor.advisor Ping Lu
dc.contributor.author Webb, Kyle
dc.contributor.department Aerospace Engineering
dc.date 2018-08-11T18:32:25.000
dc.date.accessioned 2020-06-30T03:06:48Z
dc.date.available 2020-06-30T03:06:48Z
dc.date.copyright Fri Jan 01 00:00:00 UTC 2016
dc.date.embargo 2001-01-01
dc.date.issued 2016-01-01
dc.description.abstract <p>Aeroassist guidance is concerned with providing steering commands to a vehicle flying through a planetary atmosphere in the form of an aerodynamic roll angle, or bank angle, which results in appropriate direction of the aerodynamic lift force so that the vehicle will safely and accurately reach its designated final condition. Aerocapture guidance is a particular subcategory of aeroassist guidance that involves atmospheric entry from an interplanetary transfer orbit, a guided flight through the atmosphere, and a final condition consisting of a post-atmospheric exit target orbit around the planet. Using aerocapture guidance to establish this target orbit can provide significant propellant mass savings when compared to traditional propulsive maneuvers. No current aerocapture guidance algorithms can ensure truly optimal performance in minimizing post-exit orbit insertion ΔV requirements. This thesis investigates the development of a two-phase optimal aerocapture guidance algorithm. This closed-loop guidance algorithm uses a mathematically optimal bang-bang bank angle profile structure, in which a vehicle first flies with the lift vector pointed straight up, and then flies full lift-down until atmospheric exit. The optimal trajectory is found by determining the switching time between full lift-up and full lift-down flight. Results from testing the algorithm in a high-fidelity NASA simulation environment are presented and compared with results from existing state-of-the-art aerocapture guidance algorithms. These results show that the developed algorithm provides the robustness and adaptability of a numerical predictor-corrector guidance algorithm while demonstrating a significant reduction in ΔV requirements compared to other existing algorithms.</p>
dc.format.mimetype application/pdf
dc.identifier archive/lib.dr.iastate.edu/etd/15838/
dc.identifier.articleid 6845
dc.identifier.contextkey 11165419
dc.identifier.doi https://doi.org/10.31274/etd-180810-5465
dc.identifier.s3bucket isulib-bepress-aws-west
dc.identifier.submissionpath etd/15838
dc.identifier.uri https://dr.lib.iastate.edu/handle/20.500.12876/30021
dc.language.iso en
dc.source.bitstream archive/lib.dr.iastate.edu/etd/15838/Webb_iastate_0097M_15899.pdf|||Fri Jan 14 20:47:21 UTC 2022
dc.subject.disciplines Aerospace Engineering
dc.title Evaluation of an optimal aerocapture guidance algorithm for human Mars missions
dc.type article
dc.type.genre thesis
dspace.entity.type Publication
relation.isOrgUnitOfPublication 047b23ca-7bd7-4194-b084-c4181d33d95d
thesis.degree.discipline Aerospace Engineering
thesis.degree.level thesis
thesis.degree.name Master of Science
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