FEA and Experimental Evaluation of Bonded, Riveted and Hybrid Joints in Glass Fibre Composite Laminates
FEA and Experimental Evaluation of Bonded, Riveted and Hybrid Joints in Glass Fibre Composite Laminates
FEA and Experimental Evaluation of Bonded, Riveted and Hybrid Joints in Glass Fibre Composite Laminates
PROJECT REPORT
FOR
B.E. (MECHANICAL) 8th SEM
MAJOR PROJECT
By
Rajat Saini (UE159055) Ronit Verma (UE159064)
Rishabh Panjwani (UE159059) Pratham Bhatia (UE159053)
Under the guidance of
Er. Harbhinder Singh
Faculty of Mechanical Engineering
CERTIFICATE
We hereby certify that the work which is being submitted in this report
titled “FEA and Experimental Evaluation of Bonded, Riveted and
Hybrid Joints in Glass Fiber and Jute-Glass Fibre Epoxy Composite
Laminates”, in partial fulfillment of the requirements for the award of
degree “Bachelors of Engineering in Mechanical Engineering”
submitted at UIET, Panjab University, Chandigarh, is an authentic
record of our work carried out under the supervision of “Er. Harbhinder
Singh” and refers to others’ work which are duly written in this report.
It is further certified that the report has also been thoroughly checked
on anti-plagiarism software and nothing has been found which can be
considered as plagiarism. The matter presented in this report has not
been submitted for the award of any other degree of this or any other
university.
We are also very thankful to our friends and others who in one way or
another shared their valuable support, either morally, financially and
physically.
Thanks You
ABSTRACT
OBJECTIVE :
In the present project, an attempt is made to analyze the stress
distribution in 3-D models of three configurations of single lap joint,
namely, bonded, riveted and hybrid joints and also to make an attempt
to do it experimentally by performing various tests physically.
METHODOLOGY :
Modeling and static analysis of 3-D models of the joints (bonded,
riveted and hybrid) were carried out using ANSYS FEA software. The
results were interpreted in terms of Von Mises stress.
IMPORTANCE OF THE WORK :
Composite materials have been widely used as structural elements in
aircraft structures due to their superior properties. Aircraft structure is
a huge assembly of skins, spars, frames etc. The structure consists of an
assembly of sub-structures properly arranged and connected to form a
load transmission path. Such load transmission path is achieved using
joints.
Joints constitute the weakest zones in the structure. Failure may occur
due to various reasons such as stress concentrations, excessive
deflections etc. or a combination of these. Therefore, to utilize the full
potential of composite materials, the strength and stress distribution in
the joints has to be understood so that suitable configuration can be
chosen for various applications.
Analysis using FEA tool is necessary to standardize the experimental
procedures and testing sequence.
COMPOSITE MATERIALS – AN OVERVIEW
Process carried :
3. The jute threads were added in between the two bricks until it
filled up the whole space.
4. Jute threads were evenly stretched and a with the help of a tape,
were held firmly together.
5. Glass fibre was kept on the base sheet and the mixture of resin
and hardner was applied with the help of a brush.
6. The closely packed jute threads were kept on the glass fibre.
7. Then, again, mixture of resin and hardener was applied with the
help of a brush on the jute layer.
8. On top of the jute layer, another glass fibre layer was added and
was pressed thoroughly.
9. The whole sample was left to dry for a day and more samples
were made for the longitudinal as well as cross angled (45 degree)
configurations.
2) Cutting of samples
Next step was to cut the samples. According to different ASTM codes
for various tests, the dimensions were to be cut.
For tensile tests, ASTM D638/ D3039 the total length to be taken was
165mm. Width = 20 mm and thickness = 3 mm. The common length
where the bonded, riveted and hybrid joint had to be made was 30mm.
For flexural test or bending test, ASTM D790, the total length taken =
125mm. Width = 12.7 mm and thickness was 3 mm.
For impact test (Charpy test), ASTM D256, total length = 64 mm. Width
= 2 mm.
The overlap length taken for each sample was 20 mm with reference to
the research paper :
For each type of laminate, i.e. glass fibre, jute-glass fibre longitudinal,
transverse, cross angled (45 degrees), three types of test is to be
conducted. And each type of test has three sub types of joints that is
bonded, riveted and hybrid. So total pieces cut for each type were 18.
Cutting was done with the help of Table Saw Machine.
Grinding
After the cutting of samples, for each piece, grinding was done with the
help of a grinding machine to make sure that the precision to which the
samples were cut was accurate with minimum error.
Making of joints
For bonded joints, Flex Kwik instant adhesive was used.
For riveted joints, 4 mm aluminum rivets were used with zig zag
pattern. Pitch = 12 mm and head size = 6 mm (Maximum). Riveting was
done with the help of a riveting gun.
For hybrid joint, riveting was done after the application of the
adhesive.
Rivet Gun
A rivet gun, also known as a pneumatic hammer, is a type of tool used
to drive rivets. The rivet gun is used on rivet's factory head and
a bucking bar is used to support the tail of the rivet. The energy from
the hammer in the rivet gun drives the work and the rivet against the
bucking bar. As a result, the tail of the rivet is compressed and work-
hardened. At the same time the work is tightly drawn together and
retained between the rivet head and the flattened tail (now called the
shop head, or buck-tail, to distinguish it from the factory head). Nearly
all rivet guns are pneumatically powered.
Sample types and their Orientations
(Glass Fibre)
Jute – Glass Fibre (Transverse)
+
Materials used for the various components of joints and their
properties are given below.
Component Material
Laminates Glass Fibre/Epoxy Composite
Adhesive Epoxy LY556
Hardner HY951
Glass fibre
6
Series 1
5
Series 2
4
Series 3
3
0
Honda Maruti Porche