Abstract
Ultra High Temperature Ceramic (UHTC) ZrB2- 10, 20, 30wt%SiC composites are of high interest for use in hypersonic air-breathing vehicles. In this work, ZrB2- 10, 20, 30wt%SiC UHTC composites were produced by the Spark Plasma Sintering (SPS) technique. After sintering, almost dense ceramics with ~ 5-8% porosity were produced. Their mechanical properties, such as Young’s, shear, and bulk moduli, along with Poisson’s ratio, 4-point bending strength, and single edge V-notched beam (SEVNB) fracture toughness were measured. In addition, in-situ bending experiments under a Raman microscope were performed to determine the piezo-spectroscopic coefficients of SiC Raman active peaks for calculation of thermal residual stresses. The results show that these materials are possible candidates for hypersonic airbreathing vehicles due to their high Young’s modulus, ability to withstand high temperatures, and relatively low densities.
Notes
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Graduation Date
2013
Semester
Fall
Advisor
Orlovskaya, Nina
Degree
Master of Science in Aerospace Engineering (M.S.A.E.)
College
College of Engineering and Computer Science
Department
Mechanical and Aerospace Engineering
Degree Program
Aerospace Engineering; Thermofluid Aerodynamic Systems
Format
application/pdf
Identifier
CFE0005060
URL
http://purl.fcla.edu/fcla/etd/CFE0005060
Language
English
Release Date
December 2013
Length of Campus-only Access
None
Access Status
Masters Thesis (Open Access)
Subjects
Arts and Humanities -- Dissertations, Academic, Dissertations, Academic -- Arts and Humanities
STARS Citation
Stadelmann, Richard, "Mechanical Properties And Thermal Residual Stresses Of Zrb2-sic Ceramic Composites For Hypersonic Vehicle Applications" (2013). Electronic Theses and Dissertations. 2788.
https://stars.library.ucf.edu/etd/2788