The document summarizes research conducted on using shape memory alloys (SMA) to actuate the trailing edge of an aircraft wing. It discusses SMA properties, constitutive models, experimental analysis of SMA wire behavior, wing design using CATIA, and a mechanism for converting linear SMA actuation to angular flap motion. Testing of a fabricated wing showed the SMA wire could rotate the flap 35 degrees under 660 grams of load. The research demonstrated SMA feasibility for wing control surfaces and identified areas for further optimization and testing.

1. VIDYA VIKAS INSTITUTE OF ENGINEERING & TECHNOLOGY
MYSORE
Under the Guidance of
Bharath shekar H.R
Assistant Professor
Department of Mechanical
Engineering
VVIET, Mysore
Submitted by:
1.Gowtham J 4VM11ME007
2.Manoj Kumar 4VM11ME017
3.Mohammed Uwais 4VM11ME019
4.Shreyas M N 4VM12ME410

2. INTRODUCTION
• Shape memory alloys are a unique class of metal alloys that can
recover apparent permanent strains when they are heated above a
certain temperature
• Shape memory alloys belongs to smart materials
• There are two main types of SMA:
1. Nickel titanium Alloy.
2. Copper-Aluminium Alloy.
• The discovery of the shape-memory effect were taken in the 1930s.
• A. Ölander discovered the pseudoelastic behavior of the Au-Cd
alloy in 1932.

3. INTRODUCTION

4. INTRODUCTION

5. INTRODUCTION
Figure 2: Behavior of SMA Crystals Under Deformation, Heating, and Cooling

6. INTRODUCTION
• Shape memory alloys are the advanced materials that can
be used as actuators as well as sensors.
• The characteristic features of shape memory actuators
are:
1. High energy density
2. High reversible strain makes them unique as compared to other
smart materials
• SMA “ remembers “and returns to its original shape even
if it deforms. But it is not an simple elastic material.

7. TYPES OF TRANSFORMATION
• Stress Induced Transformation
1. Super Elasticity or Psuedoelasticity Effect:
When the SMA member is loaded in pure Austenite condition,
it undergoes a transformation to detwinned Martensite state,
which also brings about a large deformation of Martensite
because of the presence of external loading.
Figure 3: Psuedoelasticity Effect in SMA

8. TYPES OF TRANSFORMATION
2. R-Phase Transformation:
During the cooling cycle of Ni-Ti alloy, an intermediate
phase called R phase is encountered just before the
Martensite phase.
• Temperature Induced Transformation
(Shape Memory Effect)
There are two kinds of shape memories that are exhibited
by an SMA member namely:
1. One- way shape memory effect
2. Two-way shape memory effect

9. TYPES OF TRANSFORMATION
1. One Way Shape Memory Effect:
When a SMA is in its cold state, the
metal can be bent or stretched &
will hold those shapes until heated
above the transmission temperature.

10. TYPES OF TRANSFORMATION
2. Two Way Shape Memory Effect:
The two way memory effect is the
effect that the material remembers
two different shapes, one at low
temperature and one at high
temperature.

11. APPLICATIONS

12. LITERATURE REVIEW
• Tanaka[1] developed a constitutive law by assuming that the strain, temperature
and the martensite volume fraction are the only state variables, and developed
the equations for the martensite volume fraction in terms of stress and
temperature.
• Liang and Roger[2] developed the martensite volume fraction using cosine
function.
• Brinson[3] developed one dimensional constitutive model for the
thermomechanical behaviour of the shape memory alloys
• Michael[4] et.al designed a new shape memory alloy actuator that possesses
impressive payload lifting capabilities.
• Peter Jardine[5] et.al developed the SMA torque tube which produced over 50 of
span-wise twist.
• Benoit Berton[6] developed the mechanism for the trailing edge shape control.
The mechanism is designed based on the original push-pull mechanism.

13. OBJECTIVE
• “To actuate the trailing edge control surface of
aircraft wing using SMA wire”.
• Primary Objective:
• Fabrication of wing according to NACA0022 standards.
• Installation of SMA wire to the wing.
• Secondary Objective:
• Conceptual design mechanism for the deployment of flap,
which converts the linear motion in to angular rotation.
• To study the behaviour of SMA wire

14. METHODOLOGY
Conclusion
Results & Discussion
Experimental Analysis
Fabrication of Wing Structure with SMA Wire
Design of Flap Actuation Mechanism
Selection of Constitutive Material Model
Generation of Wing Structure using Catia
Selection of Wing Profile

15. METHODOLOGY
• SELECTION OF WING PROFILE
The NACA airfoils are airfoil shapes for aircraft wings are developed by the
National Advisory Committee for Aeronautics, the standard wing structure
NACA0022 has been selected.
The NACA 4-digit wing sections define the profile by:
1. 1st digit describing maximum Camber as percentage of the cord.
2. 2nd digit describing the distance of maximum camber from the air foils leading
edge in 10% of the chord.
3. Last two digits describing maximum thickness of the airfoil as percent of the
chord.

16. • GENERATION OF WING STRUCTURE USING CATIA
• SELECTION OF CONSTITUTIVE MATERIAL
MODEL
The material model developed by L.C Brinson can be considered as a
benchmark. Hence it is used for further analysis.

17. METHODOLOGY
• DESIGN OF FLAPACTUATION MECHANISM
• FABRICATION OF WING STRUCTURE WITH
SMA WIRE
Aluminium Sheet of 2mm thick is used for fabrication purpose and ϕ8mm
Hinge rod is used. NiTiNol wire of 375µm is installed to the wing model.

18. METHODOLOGY
• EXPERIMENTALANALYSIS
Experimental Setup to Find Actuation Time and Load
Capacity

19. METHODOLOGY
• Experimental Setup for Stress-Strain Curve

20. RESULTS AND DISCUSSIONS
•STRESS-STRAIN BEHAVIOUR OF SMA WIRE

21. RESULTS AND DISCUSSIONS
DEFLECTION v/s LOAD
From the graph above it is observed that the wire of diameter
375µm produces an angular deflection of 35º with a maximum load
of 660 grms, for any further loading leads to decrease in actuation
capability.

22. RESULTS AND DISCUSSIONS
• TIME FOR ACTUATION
The experiment is conducted for the wire of diamete of 375µm.
From the above graph it is observed that as the load increases the
time for actuation also increases linearly. Upto 360 grms a constant
actuation time is obtained and theareafter it varies linearly with
respect to load.

23. RESULTS AND DISCUSSIONS
• TRANSFORMATION TEMPERATURES USING
K-TYPE THERMOCOUPLE

24. RESULTS AND DISCUSSIONS
• Observations
Trail 1:
Power supply is given to the circuit built and it can be
observed that it takes 4 sec for the wire to heat up or start
transforming. The voltage during these 4 sec is 1.21mV which
is converted to temperature using k-type thermocouple. After
4 sec the wire temperature reaches to 70ºC i.e. 2.93mV where
the maximum actuation is obtained. When power is cutoff it
suddenly cools, i.e. at this phase transformation takes place.
After this the wire slowly cools.
Trail 2:
Experiment is carried out same as trail 1, in this case the wire
starts loosing its property due to excessive loading and
continuous usage of the wire.

25. RESULTS AND DISCUSSIONS
• MATLAB ANALYSIS
1
2
3
4
5

26. RESULTS AND DISCUSSIONS
The above plot is generated using MATLAB codes written
according to Brinson model. It consists of variations in stress,
strain and temperature of SMA wire according to Brinson
constitutive model.
Curve (1) = Linear elastic deformation upon loading.
Curve (2) = Forward transformation upon loading.
Curve (3) = Stress reversal upon unloading.
Curve (4) = Rise in temperature to AS.
Curve (5) = Reverse transformation on increasing the
temperature to AF.

27. CONCLUSION
• The primary objective of this work is to implement the SMA wire as
an actuating member for a flap.
• The work required, the proper understanding of constitutive material
models and working with material.
• Experiments have been carried out to understand the stress-strain
behaviour of sample wire and the result obtained is satisfactory.
• Using NACA0022 the wing has been fabricated.
• The actuation of control surface is analysed using the tested wire
• The implementation is demonstrated on flap of a wing.
• The flap rotation of 350 is achieved with the proposed
mechanism.
• The Quantitative and Qualitative aspects like Stress-Strain,
Temperature, Load capacity, Time for actuation and
Frequency has been studied.

28. FUTURE SCOPE OF WORK
• The flap actuation is performed with a simple
mechanism. Hence there is a scope for further
design and its optimization.
• An optimized mechanism can be fabricated and
tested in the wind tunnel.
• The concept mechanism can be implemented for
flap actuation in small aircrafts and UAV’s.
• Composite models can be developed considering
SMA and proper resin system.

29. REFERENCES
1. Tanaka, K. “A Thermomechanical Sketch of shape memory effect one dimensional tensile
behaviour”, Res Mechanica, Elsevier publishers, vol.2, issue.3,1986, pp59-72.
2. Liang, C. “One-dimensional Thermomechanical Constitutive Relations for shape memory
materials”, Ph.d thesis, 1990, Virginia Tech.
3. L.C. Brinson, “one-dimensional constitutive behaviour of shape memory alloys:
Thermomechanical derivation with non-constant material functions and redefined martensite
internal variable”, Journal of Intelligent Material Systems and Structures, vol.4, April-1993, pp
229-241.
4. Michael, J.M, Constantinos Mavroidis, Charles Pfeiffer, “Design and dynamics of shape memory
alloy wire bundle actuator”, Proceedings of the ANS, 8th Topical meeting on Robotics and
Remote Systems, 1999
5. Jardine, AP, Bartley-Cho,JD, Flanagan,JS, “Improved design and performance of the SMA torque
tube for the DARPA smart wing program” proceedings SPIE 3674,270, Newport Beach, CA,
USA, Tuesday 02 March 1999
6. Benoit Berton, “Shape memory application: Trailing edge shape control”, Multifunctional
structures/Integration of sensors and antennas, proceedings RTO-MP-AVT-141, France, 2006, pp
13.1-13.16
7. S.H.Adarsh, U.S. Mallikarjun “Effect of variation in applied force on transformation temperatures
of NiTinol SMA’s”, Procedia Materials Science 2014, vol.5 697-703
8. FLEXINOL® Muscle Wire® Properties “DYNALLOY, Inc.” Makers of Dynamic Alloys 1562
Reynolds Avenue, Irvine, CA 92614

30. ThankYou..