Kilometer-scale Transient Atmospheres for Kinetic Payload Deposition on Icy Bodies

dc.contributor.advisorWinglee, Robert
dc.contributor.authorKoch, James Vincent
dc.date.accessioned2017-10-26T20:45:50Z
dc.date.available2017-10-26T20:45:50Z
dc.date.issued2017-10-26
dc.date.submitted2017-09
dc.descriptionThesis (Master's)--University of Washington, 2017-09
dc.description.abstractEntry, descent, and landing technologies for space exploration missions to atmospheric bodies traditionally exploit the body’s ambient atmosphere as a medium through which a spacecraft or probe can interact to transfer momentum and energy for a soft landing. For bodies with no appreciable atmosphere, a significant engineering challenge exists to overcome the lack of passive methods to decelerate a spacecraft or probe. Proposed is a novel means for the creation of a transient atmosphere for airless icy bodies through the use of a two stage payload-penetrator probe. The first stage is a hyper-velocity penetrator that impacts the icy body. The second stage is an aero-braking-capable probe directed to pass through the ejecta plume from the hyper-velocity impact. Both experimental and computational studies show that a controlled high-energy impact can direct and transfer energy and momentum to a probe via a collimated ejecta plume. In an effort to provide clarity to this unexplored class of missions, a modeling-based engineering approach is taken to provide a first-order estimation of some of the involved physical phenomena. Three sub-studies are presented: an examination and characterization of ice plumes, modeling plume-probe interaction, and the extension of plume modeling as the basis for conceptual mission design. The modeling efforts are centered about two modeling formulations: smoothed particle hydrodynamics (SPH) and the arbitrary Largrangian-Eulerian (ALE) set of techniques. A database of fully-developed hypervelocity impacts and their associated plumes is created and used as inputs to a 1-D mathematical model for the interaction of a continuum-based plume and probe. A parametric study based on the hyper-velocity impact and staging of the probe-penetrator system is presented and discussed. Shown is that a tuned penetrator-probe mission has the potential to increase spacecraft payload mass fraction over conventional soft landing schemes.
dc.embargo.termsOpen Access
dc.format.mimetypeapplication/pdf
dc.identifier.otherKoch_washington_0250O_17686.pdf
dc.identifier.urihttp://hdl.handle.net/1773/40464
dc.language.isoen_US
dc.rightsCC BY-NC
dc.subjectdrag
dc.subjectice
dc.subjectkinetic
dc.subjectmodeling
dc.subjectpenetrator
dc.subjectplume
dc.subjectAerospace engineering
dc.subjectMechanical engineering
dc.subjectApplied mathematics
dc.subject.otherAeronautics and astronautics
dc.titleKilometer-scale Transient Atmospheres for Kinetic Payload Deposition on Icy Bodies
dc.typeThesis

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