BATCH -5 BY: SANTANU DEORI KAUSHALENDRA SINGH

1. INVESTIGATION OF MECHANICAL
PROPERTIES OF RIVET JOINTS FOR GRADE 5
TITANIUM
PRESENTED BY:
SANTANU DEORI
KAUSHALENDRA SINGH

2. INTRODUCTION
In order to ensure future competitiveness in aerospace field, new generation aircraft
components and body need to have a good riveting which should relate with the
aerodynamic condition and an increase in service life and manoeuvrability. If we see
most of the aircraft body have permanent joints.
In aerospace field the rivet has a good place which cover 95% structural body
manufacturing. There are mainly two types of riveting in aerospace field:
• Solid shank rivet
• Special (blind) rivet (pop rivet)

3. ABSTRACT
Riveting has a big place in aerospace manufacturing fields. In aircraft manufacturing, it
covers 95% of aircraft body. Typical material for aircraft rivets is Aluminium alloy
(2017, 2024, 2117, 7050, 5056, 55000, v-65), Titanium and Nickel based alloy. This
paper deals with the analysis of the mechanical properties of various rivets in Titanium
grade 5 (Ti6Al4V) which are used in aircraft manufacturing. Here Solid Shank rivet
and Blind rivet are selected on Titanium grade 5 plate and both rivet joint’s tensile test,
shear stress, torsion and Charpy impact test are tested. This paper can be useful for
optimizing the rivet joints of aircraft component which are made of Titanium grade 5
and improving the productivity with a greater quality.
Keywords:: aerospace riveting, titanium grade 5 rivets properties, mechanical
properties, solid shank rivet, blind rivet.

4. [1].On the process related Rivet microstructural
evolution material flow and mechanical
properties ofTi6Al- 4V/GFRP friction Riveted
joint.
– Lucian Blagu In this paper, process related to Thermomechanical changes in the rivet
microstructure. And this paper shows the important role of friction stir welding
and its mechanical properties. This rivet done is glass fibre reinforced
polyester and Ti6Al 4V alloy. Exhibiting quasi- static lap shear strength
comparable to state of the art belted connected were investigated here. Rivet
is done in non-equilibrium B-Trane’s temperature. The combination of thermo
mechanical treatment and complex cooling regimes resulted in bi-modal micro
structural gradient in the rivet. In outside region, there were no evidence of
plastic deformation.
[2]. The Influence of clumping pressure on joint
formation and mechanical performance of Ti
alloy/ CF-PEEK friction Riveted joint. –
Natascha -Z Borbu This paper gives details the influence of pre-set clamping pressure on the joint
formation and mechanical strength of overlapping direct friction-riveted joint.
Overlapping joints using Ti6 Al 4V rivets and woven carbon fiber reinforced
polyether – ether-lectane (CF-PEEK) parts were produced. Shear force
achieved upto 6580 ± 383N over the joint.

5. [3]. Residual stress and fatigue behaviour of
riveted joint with various riveting
sequences, rivet pattern and pitcher. –
HaidayY, Bin Zheng. In this paper, the single row riveting process and triple row riveted lap
joint with their various riveted sequence are done. The fatigue life
prediction model development for multi rivet structures has been
studied in which coupling effect of stress and cyclic loads are tested. It
also tells about the fatigue cracking path of fractured specimens reveal
the correlations of the fatigue behaviour of the rivet joints.
[4]. Analysis of Rivet joint for application of
substation. –
Togesh Bagale, Lokesh
Alterade
Paper tells about FEM (Finite element method) rivet simulation. There
are 4-different type of diameter rivets are done for analysis. Tensile test
has been done for brass, aluminium and mild steel and stainless steel
using UTM. Paper also indicate that mild steel EN14 was suitable for
author work because if the diameter increases the stress gets reduced.
[5]. On the influence of the riveting process
parameters on fatigue life of Riveted Lap
joint.
Pedram Zamani This paper majorly deals with the process parameters of rivet where
author described about riveting force sheet thickness friction coefficient
and residual stress field and fatigue life for single riveted lap AF2O24
type. Increase in riveting squeeze force improves residual stress field and
increase in sheet thickness has negative effect on residual stress field.

6. [6]. Electromagnetic Riveting Technique and its
application. –
TenggiangCAU. This paper deals with the joining technique of aircraft materials in aircraft. The
analysis of joint is done for new generation aircraft. This Paper encourages to
study of electromagnetic riveting (EMR) Technique. EMR Technique
significantly improve the fatigue behaviour of mechanical joints.
[7]. Experimental Evaluation on Mechanical
properties of riveted structure with electro -
magnetic riveting. –
Xu Zhang. Hai Su. This paper deals with mechanical properties of electromagnetic riveting and
micro structure evolution was investigated by controlling deformation. The
rivet tail dimension mainly determined pull out strength and failure mode of
the riveted structure, and the optimal night of the rivet tail was 5-6 mm for
structure. The maximum load for shear test was 23.3 KN. Load to weight
ratio improved for riveted structure where for shear test it was 22.64% and for
pull out test it was 66.10%.
[8]. Structural Behaviour of aluminium self-
piercing riveted joints: An experimental and
numerical investigation.
-N-H Hoang. This paper deals with the structural behaviour of self-piercing riveted joint
based on aluminium and steel riveted. The structure was in T-shape. The
overall structural behaviour of the T-component by using aluminium rivets
under different loading conditions was comparable to those by using steel
rivets. This included also the failure made of the rivet. The ductility of the T-
component based on aluminium rivets was approximately 50% less than those
based on steel rivets. Numerical analysis showed that that peeling test used to
calibrate the SPR model parameters had minor influence on the structural
behaviour of the T-component.

7. [9]. Mechanical Properties of Self Piercing riveted (SPR) joints in
aluminium alloy 5052.
– Buoping Xing. This paper deals on the investigation into mechanical behaviour of SPR joints with different rivet
distribution patterns. For describing the SPR joint some pattern were used which are –
SSR Joint: SPR joint with single rivet
SDL Joint: SPR joint with two rivets distributed the longitudinal direction.
SDT Joint: SPR joint with two rivets distributed in the transverse direction.
SMI Joint: SPR joint with three rivets (double rivet on the right side and the single rivet on the left
side).
SMO Joint: SPR joint with three rivets (the double rivet on the left side and the single rivet on the
right side).
The strength of SDL and SDT joint improved by 88.19 and 99.59% and the ductility enhanced by
38.98 and 25.75% respectively. The strength of SMI and SMO joints improved by 175.15 and 163.34%
and the ductility reduced by 17.56 and 35.19% respectively.
[10]. Microstructure and Mechanical Property Evolution of CFRP/Al
electromagnetic riveted lap joint in severe condition.
– Hao Jiang. This paper deals with investigation of the microstructure and mechanical properties evolution of CFRP/Al
electromagnetic riveted structures exposed at a neutral salt spray environment. The electrochemical result
showed that the potential differences between the 7300 CFRP, 5182 Al sheet and 2A10 Al rivet. The potential
differences of CFRP/Al sheet, CFRP/Al rivet, Al rivet/Al sheet were
ΔU1 = 0.707V,
ΔU2 = 0.514V and
ΔU3 = 0.193V respectively.
The surface and cross section observation showed that the corrosion pits on Al sheet were mainly located at the
edge of the overlapping area. This is due to the layer potential difference between CFRP and Al and layer
clearance around the position. The maximum shear load unit & week drop faster corrosion rate confirmed by pit
depth evolution and weight exchange. Between the ageing time of 1 to 7 weeks the maximum shear load after
the ageing time of 3 weeks decreases faster due to the damage of CFRP after the damage of CFRP after long time
ageing.

8. Solid Shank Rivet
These rivets are most commonly used fastener in aviation today. It must be
driven using a bucking bar. These rivets cover 93 to 95% of aircraft body.

10. Blind Rivets
These rivets are used where impossible to use a buking bar.

11. COMPONENT
The rods and plate of titanium grade 5 (Ti-6Al-4V Alloy) were used
for both solid shank and blind rivet. Plates consists 100*100 mm
square and cylindrical rivets 5mm in diameter and 10mm long.

12. METHOD
Here we have done normal solid shank and blind riveting on titanium grade 5
metal.
By using some equipment like HUT we went through metal property testing i.e.
testing of standard specimen is subjected to a gradually increasing load (force)
until failure occurs. The resultant load-displacement behavior is used to
determine a stress–strain, from which a number of mechanical properties can be
measured.

13. TESTING
Here mainly we have tested only few mechanical properties for both the rivet’s
joint which matters a lot in aerospace field like maintaining wing twisting while
flying etc.
• Tensile test
• Torsion test
• Shear stress
• Charpy impact test

14. RESULT

15. Why are airplanes riveted and not
screwed..??
• Cheap and simple
• Impossible to open
• Flush rivets are aerodynamically good
• Can be applied from one side
• Bonding is better

16. Applications
• In aerospace field as: airplanes, missiles
• Cranes
• Hulls of ships
• Bridges
• Buildings, etc.

17. CONCLUSION
This paper has focussed on the investigation of mechanical properties of Solid shank
and blind rivet on Titanium grade 5 and explored the influence of aerodynamic
permanent joint and texture on their mechanical response. The following conclusion
can be drawn
• Both the rivet solid shank and blind rivet are properly done on titanium grade 5.
• All the given mechanical properties tested, which are tensile, shear stress and
torsion.
• And also, this paper can be useful for optimizing the rivet joints of aircraft
component which are made of Titanium grade 5 and improving the productivity
with a greater quality.

18. Thank You