Show simple item record

dc.contributor.authorSoto, Gabriel Jose
dc.date.accessioned2021-03-15T13:42:44Z
dc.date.available2021-03-15T13:42:44Z
dc.date.issued2020-12
dc.identifier.otherSoto_cornellgrad_0058F_12306
dc.identifier.otherhttp://dissertations.umi.com/cornellgrad:12306
dc.identifier.urihttps://hdl.handle.net/1813/103457
dc.description210 pages
dc.description.abstractFuture space telescopes will require more demanding requirements—such as bigger primary mirrors for higher resolution images and complex, cryo-cooled telescope designs for infrared imaging in space. To achieve these science goals, however, spacecraft science mission costs must be minimized. These include set mission times and fuel capacity which limit the amount, type, and timing of maneuvers that can be achieved. This dissertation studies both fuel and time optimal orbital techniques for (1) the delivery of space telescopes to their final orbit and (2) efficient maneuvers during space telescope observations. The first part introduces a mission concept for a segmented space telescope assembled with modular spacecraft carrying individual mirror segments. They are propelled by solar sails towards Sun-Earth L2 and then transferred onto a Lissajous orbit for assembly. I present optimal orbital procedures for computing the full trajectory design and optimal scheduling of launches to assemble the full primary mirror in a period of 11 years. The second part studies the operation of starlight suppression via starshades—an external occulter spacecraft that flies in formation with a space telescope along the line of sight to a target star and enables exoplanet direct imaging. I present analytical models for the formation flying kinematics and simulate maneuvers to remain within strict tolerances of that formation. I then present metrics and techniques for scheduling optimal observations for specific target lists that both save fuel costs and increase science output. I also study the retargeting problem: once the starshade and telescope finish an observation, the starshade must align itself with a new star. I present ways of exploring the vast search space of retargeting trajectories and apply them to the optimal scheduling of exoplanet direct imaging mission simulations.
dc.language.isoen
dc.rightsAttribution-NoDerivatives 4.0 International
dc.rights.urihttps://creativecommons.org/licenses/by-nd/4.0/
dc.subjectastrodynamics
dc.subjectexoplanets
dc.subjectoptimization
dc.subjectorbital maneuvers
dc.subjectscheduling
dc.subjecttelescopes
dc.titleOrbital Design Tools and Scheduling Techniques for Optimizing Space Science and Exoplanet-Finding Missions
dc.typedissertation or thesis
thesis.degree.disciplineAerospace Engineering
thesis.degree.grantorCornell University
thesis.degree.levelDoctor of Philosophy
thesis.degree.namePh. D., Aerospace Engineering
dc.contributor.chairSavransky, Dmitry
dc.contributor.committeeMemberRand, Richard Herbert
dc.contributor.committeeMemberNicholson, Phil
dcterms.licensehttps://hdl.handle.net/1813/59810
dc.identifier.doihttps://doi.org/10.7298/8gh5-h371


Files in this item

Thumbnail

This item appears in the following Collection(s)

Show simple item record

Except where otherwise noted, this item's license is described as Attribution-NoDerivatives 4.0 International

Statistics