Doctoral Dissertations

Abstract

"The primary objective of this research is to investigate the uncertainty in the multidisciplinary analysis of a Hypersonic Inflatable Aerodynamic Decelerator configuration for Mars entry, subject to uncertainty sources in the high-fidelity computational models and the operating conditions. Efficient uncertainty quantification methods based on stochastic expansions are applied to the analysis of the hypersonic flowfield, fluid-structure interaction, and flexible thermal protection system response of a deformable inflatable decelerator. Uncertainty analysis is first applied to the hypersonic flowfield simulations to quantify the uncertainty in the surface convective and radiative heat flux, pressure, and shear stress of a fixed inflatable decelerator, subject to uncertainties in the binary collision integrals of the transport properties, chemical kinetics, non-Boltzmann radiation modeling, and the freestream conditions. The uncertainty analysis for fluid-structure interaction modeling is conducted to quantify the uncertainty in the deflection and resulting surface heat flux, shear stress, and pressure of a deformable inflatable decelerator, subject to uncertainties in material structural properties, inflation pressure, and important flowfield uncertain variables identified in the initial study. The deflection uncertainty is shown to be primarily driven by the structural modeling uncertain variables and found to be insignificant in contributing to the resulting surface condition uncertainties. Uncertainty analysis is finally applied to the flexible thermal protection system bondline temperature for a ballistic Mars entry trajectory, subject to uncertainties in the material thermal properties and important flowfield variables from the initial study. The uncertainty in the bondline temperature is compared to its allowable temperature limit and shown to be primarily driven by the material thermal properties of the outer fabric and insulator layers, and the freestream density"--Abstract, page iv.

Advisor(s)

Hosder, Serhat

Committee Member(s)

Riggins, David W.
Isaac, Kakkattukuhzy M.
Du, Xiaoping
Maddalena, Luca

Department(s)

Mechanical and Aerospace Engineering

Degree Name

Ph. D. in Aerospace Engineering

Sponsor(s)

United States. National Aeronautics and Space Administration

Publisher

Missouri University of Science and Technology

Publication Date

Fall 2016

Journal article titles appearing in thesis/dissertation

  • Uncertainty analysis of Mars entry flows over a hypersonic inflatable aerodynamic decelerator
  • Uncertainty analysis of fluid-structure interaction of a deformable hypersonic inflatable aerodynamic decelerator
  • Thermal protection system uncertainty of a hypersonic inflatable aerodynamic decelerator

Pagination

xvi, 155 pages

Note about bibliography

Includes bibliographic references.

Rights

© Andrew J. Brune

Document Type

Dissertation - Open Access

File Type

text

Language

English

Library of Congress Subject Headings

Space shuttles -- Payloads -- Analysis
Fluid-structure interaction
Space vehicles -- Thermal properties

Thesis Number

T 11016

Electronic OCLC #

974709724

Comments

This work was supported by a NASA Space Technology Research Fellowship under training grant no. NNX13AL58H

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