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NUMERICAL SIMULATION OF FRACTURE OF A NANO-PAPER COATED E-GLASS/POLYESTER COMPOSITE WITH THERMAL DAMAGE

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Date Issued:
2013
Abstract/Description:
Aerospace research for next-generation travel increasingly focuses on the use of advanced composites to reduce weight and cost while retaining strength. One subset of materials with great potential is based on the combination of resin matrix and glass-fiber reinforcement. This research explores the application of a candidate nanopaper coating with a given composite. Prior research applied a set of given heat fluxes to the top surface of the composite for a set of given periods of time, and subsequently performed a 3-point flexural test to determine the elastic modulus for both the coated and uncoated composite for all of the combinations of heat flux and time. A finite element (FE) model is developed using the ANSYS general purpose finite element analysis (FEA) software that models the degradation in strength/stiffness properties based on heating condition and with the goal of predicting cracking using the element death feature in ANSYS. This thesis describes the prior research suggesting both the need for and novelty of this model, and the procedures used to form the model. The loading conditions of the 3-point flexural test are replicated, and four measures of accuracy are developed based on the force versus displacement curve of the test and the FE model. It is envisioned that continuum-level models developed as a part of these research be applied for design of next-generation space components These measurements are used to verify the FE model, and this model is then employed to extrapolate beyond the context of experimental conditions.
Title: NUMERICAL SIMULATION OF FRACTURE OF A NANO-PAPER COATED E-GLASS/POLYESTER COMPOSITE WITH THERMAL DAMAGE.
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Name(s): Graham, Zachary, Author
Gordon, Ali, Committee Chair
University of Central Florida, Degree Grantor
Type of Resource: text
Date Issued: 2013
Publisher: University of Central Florida
Language(s): English
Abstract/Description: Aerospace research for next-generation travel increasingly focuses on the use of advanced composites to reduce weight and cost while retaining strength. One subset of materials with great potential is based on the combination of resin matrix and glass-fiber reinforcement. This research explores the application of a candidate nanopaper coating with a given composite. Prior research applied a set of given heat fluxes to the top surface of the composite for a set of given periods of time, and subsequently performed a 3-point flexural test to determine the elastic modulus for both the coated and uncoated composite for all of the combinations of heat flux and time. A finite element (FE) model is developed using the ANSYS general purpose finite element analysis (FEA) software that models the degradation in strength/stiffness properties based on heating condition and with the goal of predicting cracking using the element death feature in ANSYS. This thesis describes the prior research suggesting both the need for and novelty of this model, and the procedures used to form the model. The loading conditions of the 3-point flexural test are replicated, and four measures of accuracy are developed based on the force versus displacement curve of the test and the FE model. It is envisioned that continuum-level models developed as a part of these research be applied for design of next-generation space components These measurements are used to verify the FE model, and this model is then employed to extrapolate beyond the context of experimental conditions.
Identifier: CFH0004346 (IID), ucf:45021 (fedora)
Note(s): 2013-05-01
B.S.M.E.
Engineering and Computer Science, Dept. of Mechanical, Materials and Aerospace Engineering
Bachelors
This record was generated from author submitted information.
Subject(s): finite
element
analysis
finite element analysis
composite
eglass
e-glass
polyester
eglass/polyester
e-glass/polyester
thermal
damage
thermal damage
nano
paper
nanopaper
nano-paper
coated
coating
ANSYS
element death
element birth
flexural
three-point bend
three-point bending
bending
Persistent Link to This Record: http://purl.flvc.org/ucf/fd/CFH0004346
Restrictions on Access: public
Host Institution: UCF

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