PPT

1. “Strength estimation of E-glass and carbon fiber composite comparative analysis and
performance evaluation”
Department of Aeronautical Engineering
PROJECT PRESENTATION
Guided by
Mr. Ram Vishal
Assistant Professor
Department of Aeronautical Engineering
19-10-2023
Student name USN
Pragathi BS 1NT20AE041
SHASHI KUMAR S 1NT21AE408
SHREE NARESH 1NT20AE061

2. 19-10-2023 Department of Aeronautical Engineering 2
Contents
• Introduction
• Literature survey
• Research gap
• Objectives
• Methodology
• References

3. 19-10-2023 Department of Aeronautical Engineering 3
Abstract
This project describes the materials and the methods used to make a tensile test and flexure test of composite material. The
experimental study is conducted to observe the fracture of composite material using different types of material namely:
glass lamination and carbon fibers specimens. Then, the behavior of the composite specimens is observed to determine the
best material that produced the highest mechanical properties . then repairing with homogeneous and non homogeneous
materials and comparison between them . The experimental work has been divided into two stages. The first stage is the
experimental process, which involves fabrication of the specimens for the tensile test and flexure test. The second stage is
repair of specimens and testing of repaired specimens.

4. 19-10-2023 Department of Aeronautical Engineering 4
Introduction
• In the domain of aircraft design and engineering, the selection of materials plays a pivotal role in determining the overall
performance, efficiency, and safety of the aircraft. This introduction delves into the significance of homogeneous carbon
fiber, glass laminates, and their combined composite in the context of aircraft applications. These materials are at the
forefront of innovation, promising to address the demanding requirements of the aerospace industry.
• Homogeneous carbon fiber, known for its exceptional strength-to-weight ratio and resistance to fatigue, stands as a
promising candidate for aircraft components. Its utilization aims to enhance structural integrity while minimizing overall
weight—a critical factor in aircraft efficiency.
• Glass laminates, renowned for their versatility and cost-effectiveness, offer unique properties that cater to specific
structural needs in aircraft design. Their application is often strategic, providing a balance between performance and
economic considerations.

5. Introduction
• The combination of homogeneous carbon fiber and glass laminates represents a synergistic approach, seeking to
hardness the strengths of both materials. This composite not only aims to optimize structural performance but also
addresses factors such as cost-effectiveness and manufacturability in the context of aircraft applications.
• As the aerospace industry continually pushes the boundaries of innovation, the exploration of homogeneous
carbon fiber, glass laminates, and their composite holds the promise of revolutionizing aircraft design. This study
embarks on a journey to assess the individual merits of these materials and uncover the potential enhancements
achieved through their combination, ultimately contributing to the evolution of materials used in modern aircraft.
5

6. LITERATURE REVIEW
191023 6
Sl.
No.
Title & Author(s) Objectives Methodology Outcomes Remarks
1.
Processing and
Flexural Strength of
Carbon Fiber and
Glass Fiber
Reinforced Epoxy-
Matrix Hybrid
Composite
(Prashanth Turla , S.
Sampath Kumar, P.
Harshitha ) -2014
• To investigate the flexural
strength of a hybrid epoxy
matrix composite reinforced
with both glass and carbon
fibres.
• To understand the individual
influences of glass and carbon
fibres on the flexural strength
by preparing and extensively
studying carbon Fiber epoxy
and glass fibre epoxy
composites
• 1. Investigate flexural strength in
hybrid epoxy matrix composite with
glass and carbon fibres.
• 2. Examine individual effects of
glass and carbon fibres using
prepared carbon fibre epoxy and
glass fibre epoxy composites.
• 3. Perform a comparative analysis,
highlighting significant
enhancement in flexural strength of
the hybrid composite compared to
glass and carbon fibre-reinforced
counterparts.
• Processed hybrid, glass, and
carbon fiber epoxy
composites using filament
winding.
• Hybrid composite excels in
flexural strength, ideal for
aerospace structures.
• Glass composite excels in
flexural strength, surpassing
brittle carbon counterpart.
• Filament winding
process complexity.
• Potential production
cost for hybrid
composite.
• Limited flexibility
in adapting to
dynamic aerospace
requirements.
2.
• Interlaminar Shear
Strength of Carbon
Fiber and Glass
Fiber Reinforced
Epoxy Matrix
Hybrid Composite
(Prashanth Turla ,
S. Sampath Kumar
• Investigate interlaminar
shear strength (ILSS) of glass
and carbon fiber epoxy
matrix hybrid composite.
• Assess individual influences
of glass and carbon fibers on
ILSS in carbon fiber epoxy
and glass fiber epoxy
composites.
• To study ILSS of glass and carbon
fiber epoxy matrix hybrid
composite.
• To assess individual influences of
glass and carbon fibers on ILSS in
carbon fiber epoxy and glass fiber
epoxy composites.
• To repare and extensively study
carbon fiber epoxy and glass fiber
• Interlaminar shear strength
evaluation showed
significantly higher values
for the three-phase glass-
carbon fiber reinforced
epoxy matrix hybrid
composite compared to the
two-phase glass and carbon
fiber reinforced epoxy
• The three-phase
hybrid composite
may face challenges
such as increased
complexity in
manufacturing and
potential cost
implications
compared to the

7. LITERATURE REVIEW
17 March 2024 7
Sl.
No.
Title & Author(s) Objectives Methodology Outcomes Remarks
3.
Optimisation study of
tapered scarf and
stepped-lap joints in
composite repair
patches( Hamza
Bendemra , Paul
Compston , Phillip J.
Crothers) -2015
• to analyse stepped-lap and
tapered scarf repairs in
composite structures. It involves
investigating design parameters,
conducting linear finite element
analysis, and assessing
sensitivity to factors
• To determine a critical overply
lap length crucial for optimizing
joint performance
• Linear Finite Element Analysis
• analyzing the sensitivity of
tapered scarf and stepped-lap
joints to ply thickness, taper
angle
.stepped-lap joints inherently
exhibit higher stress
concentration than equivalent
tapered scarf joints.
Encouragingly, the introduction
of overplies and strategic design
adjustments effectively
mitigates stress peaks at joint
tips and step corners, offering a
practical solution to enhance the
mechanical performance of
stepped-lap joints and improve
structural integrity in composite
repairs.
• Complex Optimization
• Overplies Limitation
• Increased Complexity
• Increased Analysis
Complexity
4.
Experimental
Investigation of Bi
directional Carbon
Fiber Composite-
2015 (J.Dhanraj
Pamara B.Balu
Naikb O.Hema
Lathac G.M. Sayeed
• To explore the mechanical
properties of bi-directional
carbon fiber composites.
• Investigate the influence of fiber
orientation in laminates on these
properties.
• Conduct experimentation to
gather empirical data and
• Understanding Mechanical
Properties
• Analysing Fiber Orientation
• Experimental Data Collection
• Compliance with Standards
• Tensile and Flexural Testing
• Graphical Documentation
• In this experimental
investigation, the 90º
orientation exhibits superior
tensile properties, requiring
more force for fracture. Off-
axis loading in 30º and 45º
orientations results in
increased displacement and
• Off-axis loading
causes higher
displacement, stress
concentration, and
premature failure due
to considerable fiber
pull-out before fracture
in non-90º

8. LITERATURE REVIEW
191023 8
Sl.
No.
Title & Author(s) Objectives Methodology Outcomes Remarks
5.
DEVELOPMENT
AND TESTING OF
GLASS FIBRE
REINFORCED
COMPOSITES
(Saichand Kotla
Rachana K)-2020
• Create a composite material by
reinforcing glass fibers in an
epoxy matrix.
• Conduct extensive testing,
including tensile and impact
strength, as well as Young's
modulus of elasticity.
• Compare and analyze the test
results to find the composite
with the best properties.
• to choose composites with high
strength and ductility for
possible usage in a variety of
structural applications.
• Material Selection
• Composite Fabrication
• Sample Preparation
• Testing(Impact Strength,
Young's Modulus,
Tensile Strength )
• Data Collection
• Comparison and
Analysis
• Optimal Composite
Selection
• The composite material exhibits
superior tensile strength at 30º
orientation, with lower strength at
90º. In compression, 0º orientation
excels, while 30º remains
competitive. The overall best
orientation is 30º.
• Lower tensile strength
may have an influence
on overall
performance and
structural integrity in
applications where
components receive
tensile stresses along
a 90º orientation, such
as wing structures in
airplanes..
6.
• On fatigue stress-
cycle curves of
carbon, glass and
hybrid carbon/glass
reinforced fibre
metal laminates
(Konrad Dadej ,
• To predict and validate static
and fatigue strength of
conventional and hybrid fiber
metal laminates.
• To demonstrate that
glass/carbon hybrid laminates
have lower static but higher
fatigue strength than current
• Static and Fatigue
Strength Prediction
• Comparison of Hybrid
Laminates
• Theoretical and
Experimental Validation
• Carbon/glass hybridization
enhances the mechanical fatigue
resistance of FMLs over GLARE-
type laminates. High metal layer
contribution decreases fatigue life,
which has an influence on total
high-cycle resistance. CARALL
laminates with high stiffness carbon
• Metal Layer
Drawback
• Stress-Cycle
Complexity
• Hybridization
Challenges

9. LITERATURE REVIEW
191023 9
Sl.
No.
Title & Author(s) Objectives Methodology Outcomes Remarks
7.
Interlaminar Shear
Strength of Carbon
Fiber and Glass
Fiber Reinforced
Epoxy Matrix
Hybrid Composite
(Prashanth Turla ,
S. Sampath Kumar ,
P. Harshitha Reddy
, K. Chandra
Shekar) -2014
• Investigate interlaminar shear
strength (ILSS) of glass and
carbon fiber epoxy matrix
hybrid composite.
• Assess individual influences
of glass and carbon fibers on
ILSS in carbon fiber epoxy and
glass fiber epoxy composites.
• Compare ILSS of hybrid
composite with glass fiber
reinforced and carbon fiber
reinforced composites to
determine improvements.
• To study ILSS of glass and
carbon fiber epoxy matrix
hybrid composite.
• To assess individual influences
of glass and carbon fibers on
ILSS in carbon fiber epoxy and
glass fiber epoxy composites.
• To repare and extensively study
carbon fiber epoxy and glass
fiber epoxy composites.
• To compare and analyze ILSS
of hybrid composite with glass
fiber and carbon fiber
reinforced composites to
determine improvements.
• Interlaminar shear strength
evaluation showed significantly
higher values for the three-phase
glass-carbon fiber reinforced epoxy
matrix hybrid composite compared
to the two-phase glass and carbon
fiber reinforced epoxy matrix
composites, indicating the
advantage of hybridization.
• The three-phase
hybrid composite
may face
challenges such as
increased
complexity in
manufacturing and
potential cost
implications
compared to the
simpler two-phase
composites.
8
On fatigue stress-
cycle curves of
carbon, glass and
hybrid carbon/glass
reinforced fibre
metal laminates
• 1. To predict and validate static
and fatigue strength of
conventional and hybrid fiber
metal laminates.
• 2. To demonstrate that
glass/carbon hybrid laminates
have lower static but higher
• Static and Fatigue Strength
Prediction
• Comparison of Hybrid Laminates
• Theoretical and Experimental
Validation
• Carbon/glass hybridization
enhances the mechanical fatigue
resistance of FMLs over GLARE-
type laminates. High metal layer
contribution decreases fatigue life,
which has an influence on total
high-cycle resistance. CARALL
• Metal Layer
Drawback
• Stress-Cycle
Complexity
• Hybridization
Challenges

10. Critical review of literature and identified
research gaps
The literatures gives an in-depth knowledge on
This literature review provides a foundation for understanding the key aspects of composite material
development, testing, repair methodologies, and strength estimation. It forms the basis for the
proposed research project on the development, testing, and repair of glass fiber laminates and
carbon fiber laminates with a focus on strength estimation using homogeneous and hybrid
materials.
10

11. RESEARCH GAP
• RESEARCH GAP
11
While existing studies extensively cover the development, testing, and repair of glass fiber
laminates (GFL) and carbon fiber laminates (CFL), a significant gap exists in
systematically exploring strength estimation for repairs with homogeneous and hybrid
materials. Current literature often overlooks the optimization of repair methodologies,
particularly lacking in comparative assessments of materials for restoring damaged
laminates. This research addresses these gaps, offering a holistic perspective on the life
cycle of GFL and CFL, emphasizing strength estimation in diverse material repairs.

12. Objectives
19-10-2023 Department of Aeronautical Engineering 12
• Development Phase:
• Fabricate high-quality glass fiber laminates (GFL) and carbon fiber laminates (CFL) with precision,
adhering to industry standard
• Testing Phase:
• Conduction of mechanical testing, including tensile strength, flexural strength to characterize the
baseline properties of GFL and CFL.
• Establish a robust dataset for subsequent evaluation and comparison of repaired laminates.
• Repair Methodologies:
• Investigate and implement cutting-edge repair techniques for damaged GFL and CFL, utilizing
homogeneous materials for one set of repairs.
• Explore the effectiveness of hybrid materials, combining glass and carbon fibers, in another set of
repairs.

13. Objectives
• Strength Estimation:
• Systematically analyze the strength of repaired laminates through experimental testing and
computational simulations.
• Quantify and compare the effectiveness of homogeneous and hybrid materials in restoring
the mechanical properties of damaged laminates.
• Optimization and Guidelines:
• Develop guidelines for selecting optimal repair methodologies based on the observed
strengths and weaknesses of homogeneous and hybrid material repairs.
• Optimize repair processes to maximize structural restoration and enhance the overall
performance of GFL and CFL.
13

14. METHODOLOGY
19-10-2023 Department of Aeronautical Engineering 14
• Selection of materials :The materials like carbon Fiber and glass fibers of 5 layers laminated by vaccum bagging process with
thickness 1.5 mm as per GSM and ASTM standards
• Design of specimen: Selecting suitable joints for before and after failure of the specimen. scarf repairs provide a significant
recovery of residual strength in damaged composite and also double lap joints.
• Fracture of designed specimen: By using Universal testing machine conducting tensile test and bending test to known ultimate
strength and young's 'modulus
• Repair with homogeneous and non- homogeneous: After breaking the specimen repaired with two different specimen a
suitable adhesive bond
• Testing of repaired material: conducting 10 trails of testing for carbon-fiber specimen and also for glass laminated composites
• Comparison of result for homogeneous and non- homogeneous repair: evaluating the each graph and to known which is
better.

15. Glass fiber
Glass fiber Vaccum bagging process
15

16. Glass fiber
specimen before test Tensile test specimen after test
16

17. Glass fiber microscopic under
microscopic view
17

18. Glass fiber laminates under
microscopic view
18

19. Calculation of stress
19

20. Stress vs Strain
20
0
5
10
15
20
25
0 1 2 3 4 5 6 7
STRESS
STRAIN
STRESS VS STRAIN
Extensometer Elongation Time Frequency Pressure Flow Stress Strain Series9

21. Load vs Stress
21

22. REFERENCES
19-10-2023 Department of Aeronautical Engineering 22
1]. Processing and Flexural Strength of Carbon Fiber and Glass Fiber Reinforced Epoxy-Matrix Hybrid Composite (Prashanth Turla , S. Sampath Kumar, P. Harshitha ) -2014
2]. Interlaminar Shear Strength of Carbon Fiber and Glass Fiber Reinforced Epoxy Matrix Hybrid Composite (Prashanth Turla , S. Sampath Kumar , P. Harshitha Reddy , K. Chandra
Shekar) -2014
3] Optimisation study of tapered scarf and stepped-lap joints in composite repair patches( Hamza Bendemra , Paul Compston , Phillip J. Crothers) -2015
4] Interlaminar Shear Strength of Carbon Fiber and Glass Fiber Reinforced Epoxy Matrix Hybrid Composite (Prashanth Turla , S. Sampath Kumar , P. Harshitha Reddy , K. Chandra
Shekar) -2014
5] On fatigue stress-cycle curves of carbon, glass and hybrid carbon/glass reinforced fibre metal laminates (Konrad Dadej , Jarosław Bieniaś) -2020
6] Al-Mahaidi, R., & Zhao, X. L. (2013). Recent Developments in Hybrid FRP Composites: Rehabilitation and Retrofitting of Structures. Composite Structures,
7] Barbero, E. J. (2015). Introduction to Composite Materials Design (2nd ed.).
8] Gibson, R. F., & Schreier, H. W. (2016). Composites Research in the Twenty-First Century: A Perspective. Journal of the American Ceramic Society, 99(1), 1–14.
9] Chawla, K. K. (2012). Composite Materials: Science and Engineering. Springer
10] Yousif, B. F., & Ku, H. (2013). Flexural Behaviour of Hemp/Epoxy Composite Thin Laminates. Materials & Design, 45, 319–326.
11] Kalamkarov, A. L., & Andrianov, I. V. (2017). Hybrid Anisotropic Materials for Structural Aviation Applications: A Review. Composite Structures, 160, 815–832.
12] Zhang, H., & Teng, J. G. (2013). Strengthening of RC Structures Using Externally Bonded FRP Composites in Flexure: A State-of-the-Art Review. Engineering Structures, 47, 54–67.

23. Thank you.
Aeronautical Engineering