Masters Theses

Abstract

"Composites materials are increasingly being used in aerospace applications over the past few years. The unique properties like high strength to weight ratio, thermal stability, fatigue and corrosion resistance set them apart from the conventional materials. Composite materials are well suited for the applications where weight is the primary concern in the design. Composites structures are vulnerable to mechanical as well as thermal loadings. Transverse micro-cracking and delamination are the most common type of failures in composite materials. The thickness of the ply being used play a key role dictating the properties of the resultant composite structure. As the ply gets thinner the properties get better. Thick laminates are more susceptible to micro-cracking than thin laminates. Thereby, to manufacture laminates resistant to micro-cracking and delamination it is advised to use thinner plies. In this work, a BMI hardened prepreg system was used to prepare the laminated composites. Thin and thick ply laminates were used to make the composite panels .Mechanical testing was performed on the panels to evaluate the performance of thin-ply and thick-ply laminate system"--Abstract, page iv.

Advisor(s)

Chandrashekhara, K.

Committee Member(s)

Chen, Lianyi
Dharani, Lokeswarappa R.

Department(s)

Mechanical and Aerospace Engineering

Degree Name

M.S. in Mechanical Engineering

Sponsor(s)

Technical Data Analysis, Inc.

Comments

This work is funded by Technical Data Analysis Inc., (TDA), Falls Church, VA 22042.

Publisher

Missouri University of Science and Technology

Publication Date

Summer 2019

Pagination

ix, 27 pages

Note about bibliography

Includes bibliographic references.

Rights

© 2019 Manoj Kumar Reddy Rangapuram, All rights reserved.

Document Type

Thesis - Open Access

File Type

text

Language

English

Thesis Number

T 11723

Electronic OCLC #

1164805576

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