Kilometer-scale Transient Atmospheres for Kinetic Payload Deposition on Icy Bodies
| dc.contributor.advisor | Winglee, Robert | |
| dc.contributor.author | Koch, James Vincent | |
| dc.date.accessioned | 2017-10-26T20:45:50Z | |
| dc.date.available | 2017-10-26T20:45:50Z | |
| dc.date.issued | 2017-10-26 | |
| dc.date.submitted | 2017-09 | |
| dc.description | Thesis (Master's)--University of Washington, 2017-09 | |
| dc.description.abstract | Entry, 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.terms | Open Access | |
| dc.format.mimetype | application/pdf | |
| dc.identifier.other | Koch_washington_0250O_17686.pdf | |
| dc.identifier.uri | http://hdl.handle.net/1773/40464 | |
| dc.language.iso | en_US | |
| dc.rights | CC BY-NC | |
| dc.subject | drag | |
| dc.subject | ice | |
| dc.subject | kinetic | |
| dc.subject | modeling | |
| dc.subject | penetrator | |
| dc.subject | plume | |
| dc.subject | Aerospace engineering | |
| dc.subject | Mechanical engineering | |
| dc.subject | Applied mathematics | |
| dc.subject.other | Aeronautics and astronautics | |
| dc.title | Kilometer-scale Transient Atmospheres for Kinetic Payload Deposition on Icy Bodies | |
| dc.type | Thesis |
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