High-fidelity modeling and impact footprint prediction for vehicle breakup analysis.
| dc.contributor.advisor | Tuckness, Dan G., | en_US |
| dc.contributor.author | Ling, Lisa. | en_US |
| dc.date.accessioned | 2013-08-16T12:19:54Z | |
| dc.date.available | 2013-08-16T12:19:54Z | |
| dc.date.issued | 2005 | en_US |
| dc.description.abstract | Thus the main thrust of this study was to develop and verify the additional dynamics modeling and capabilities for the analysis tool with the objectives to (1) have the capability to predict impact point and footprint, (2) increase the fidelity in the prediction of vehicle breakup, and (3) reduce the effort and time required to complete an analysis. The new functions developed for predicting the impact point and footprint included 3-degrees-of-freedom trajectory propagation, the generation of non-arbitrary entry conditions, sensitivity analysis, and the calculation of impact footprint. The functions to increase the fidelity in the prediction of vehicle breakup included a panel code to calculate the hypersonic aerodynamic coefficients for an arbitrary-shaped body and the modeling of local winds. The function to reduce the effort and time required to complete an analysis included the calculation of node failure criteria. The derivation and development of these new functions are presented in this dissertation, and examples are given to demonstrate the new capabilities and the improvements made, with comparisons between the results obtained from the upgraded analysis tool and the legacy software wherever applicable. | en_US |
| dc.description.abstract | For decades, vehicle breakup analysis had been performed for space missions that used nuclear heater or power units in order to assess aerospace nuclear safety for potential launch failures leading to inadvertent atmospheric reentry. Such pre-launch risk analysis is imperative to assess possible environmental impacts, obtain launch approval, and for launch contingency planning. In order to accurately perform a vehicle breakup analysis, the analysis tool should include a trajectory propagation algorithm coupled with thermal and structural analyses and influences. Since such a software tool was not available commercially or in the public domain, a basic analysis tool was developed by Dr. Angus McRonald prior to this study. This legacy software consisted of low-fidelity modeling and had the capability to predict vehicle breakup, but did not predict the surface impact point of the nuclear component. | en_US |
| dc.format.extent | xii, 158 leaves : | en_US |
| dc.identifier.uri | http://hdl.handle.net/11244/910 | |
| dc.note | Source: Dissertation Abstracts International, Volume: 66-06, Section: B, page: 3252. | en_US |
| dc.note | Adviser: Dan G. Tuckness. | en_US |
| dc.subject | Space vehicles Atmospheric entry. | en_US |
| dc.subject | Space vehicles Nuclear power plants. | en_US |
| dc.subject | Engineering, Aerospace. | en_US |
| dc.thesis.degree | Ph.D. | en_US |
| dc.thesis.degreeDiscipline | School of Aerospace and Mechanical Engineering | en_US |
| dc.title | High-fidelity modeling and impact footprint prediction for vehicle breakup analysis. | en_US |
| dc.type | Thesis | en_US |
| ou.group | College of Engineering::School of Aerospace and Mechanical Engineering | |
| ou.identifier | (UMI)AAI3179077 | en_US |
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