Development of Asymmetrical Flapping Mechanism for Flapping Wing MAV

This project explains the development of the asymmetrical flapping mechanism for the flapping wing MAV. The objectives were to develop the mechanism and assess its effectiveness for a given frequency range. The author's major area of work was to develop the mechanism and test the model. The project group consisted of team members. The author applied complex problem solving, judgment, decision making, operations analysis, and system analysis skills. The issues faced were installation of the flapping wings and asymmetrical flapping mechanism. The solutions provided were to exhibit proper forward flight capability and carry light weighted equipments. The plan was to bring out creative and innovative work by working mutually.

CE 2.1 Project Information
Name of the project: Development of Asymmetrical Flapping Mechanism for
Flapping Wing MAV
Location of the project: Please fill
Project Duration: From January of 2015 to April of 2015
Organization: Please fill
Role and Designation during the time: Team Member of the project
CE 2.2 Project Background
CE 2.2.1 Characteristics of the project
This project of Development of Asymmetrical Flapping Mechanism for Flapping
Wing MAV was my second major project in aeronautical engineering career. The
incrementing demand of the miniaturization within vehicles for the better performance has
eventually brought the overall attention of the flapping wing aerodynamics within the field of
MAV or micro air vehicles. This project has explained the significant development of the
asymmetrical flapping mechanism for the flapping wing MAV. We have used kinematics for
the four bar mechanism where crank level and the slotted lever mechanism were utilized. The
effectiveness of asymmetrical flapping in the domain of flapping wing MAV for a frequency
range of 3 Hz to 12 Hz over a range of varying time ratios from 1.58 to 3.05 was assessed in
the project.

CE 2.2.2 Objectives developed for the project
The project of Development of Asymmetrical Flapping Mechanism for Flapping
Wing MAV comprised of two important objectives. They are given below:
 To develop an asymmetrical flapping mechanism for the flapping wing MAV.
 To assess the effectiveness of asymmetrical flapping in the domain of flapping wing
MAV for a given frequency range.
 To study and observe the smoke flow visualization of the asymmetric flapping wing
MAV.
CE 2.2.3 My area of work
My major area of work in this project of Development of Asymmetrical Flapping
Mechanism for Flapping Wing MAV was to develop the asymmetrical flapping mechanism. I
even tested the model in the normal atmospheric conditions and check up the speed or other
wind tunnel conditions. My other areas of work were checking the advance ratio of the
project and generation of more lift or thrust whenever the flight was in unsteady state.
Moreover, I even developed the lift generation mechanism in this project.

CE 2.2.4 Project Group
Figure 1: People involved in the project
CE 2.2.5 My responsibilities throughout the project
I was an important part of the project. I had various important responsibilities within
the project. My first and foremost responsibility in this project of Development of
Asymmetrical Flapping Mechanism for Flapping Wing MAV was to develop the significant
mechanism of flapping mechanism in MAV or micro air vehicles. I knew that if this
mechanism will not be executed properly, the entire project would be at stake. Hence, I
ensured that this project is well executed without any type of complications. Mu next
responsibility was to learn about the flapping aerodynamics. The flapping wings MAV were
utilized in this particular project. Furthermore, my other responsibilities involved checking
the advanced ratio in the project and make sure that the ratio is perfect. I was successful in
executing all of the responsibilities perfectly and properly.

CE 2.3 Distinctive Activity
CE 2.3.1 Engineering knowledge and skills applied in the project
I have utilized my aeronautical engineering skills and knowledge in this particular
project of Development of Asymmetrical Flapping Mechanism for Flapping Wing MAV. The
most important aeronautical engineering skill that I have applied in the project was complex
problem solving. It helped me in indentifying the various complex problems and reviewed the
related information or data for the development or evaluation of options and implementation
of solutions. The judgment as well as decision making skills was also applied here.
Moreover, I have even applied operations analysis and system analysis properly. Physics and
mathematics were always my strong points and I was able to use them as my strengths. My
computer proficiencies helped me in run the software easily and get error free results.
CE 2.3.3 Comprehending the Theory of Project
The flapping flight could be extremely complicated than the flight with the fixed
wings. This is mainly of the several structural movements as well as the resulting fluid
dynamics. In the flapping flight, these wings could move forward with the air and even flap
up or down, sweep, bend and twist. Since the specific wing twists, the outer rim of this wing
can move downward, this lift force within the outer rim of this wing is being angled forward.
The overall mechanism of MAV is extremely important since it is responsible for
affecting the lift features of a vehicle. The major factors such as the flap angle, flapping
frequencies, dependency on proper designing of this mechanism. The design parameters of
this project were flap angle, crank diameter and offset distance. Asymmetrical flapping helps
in maintaining the constant motor torques, and hence helps to reduce the motor load. The lift
for down stroke of this wing eventually acts in the most favorable direction since it
increments the motor torques.

The increasing order of performance depends much on the aspect ratio rather than the
wing platform shape of the wing. The overall aerodynamic performances like time based lift
or thrust or drag generation of the two flexible wings with the separate skin flexibilities were
being compared to those of the conventional rigid wings for assessing the total effects of skin
flexibilities of the examined wings over their basic aerodynamic performances for the
applications of flapping flight.
In the flapper design we have used crank and slotted lever quick return mechanism.
This is the mechanism which is used in shaper machine. It consists of a connecting road,
crank, slotted lever and a slider. The slider pin is located in the crank and it goes into the
slotted lever. The time for forward stroke and return stroke is different and it depends on the
offset with which the slotted lever is positioned, and the crank diameter.

Table 1: Mechanism of Crank and Slotted Lever
The 3D modeling of the mechanism of the project with the help of software of Solid
Works was done perfectly. The model consists of a frame for holding the gears and linkages,
gears, motor and slotted lever. The cranks are provided with holes at different
diameters(16mm, 22mm, 23mm and 24mm), so that the time ratio can be changed by
changing the holes which connects the slotted lever to the crank. The slotted lever is
connected in front of the crank.
Table 2: Specification of the model
Mylar was used for wing profile, thus wing section was attached to the assembled
mechanism and the MAV was ready for testing. The developed MAV was tested in Wind off
condition and Wind on conditions. These data were analyzed and interpreted. Taking the
symmetric flapping wing MAV as a baseline for our experiment, developed asymmetric
flapping wing MAV is compared with baseline symmetric mechanism and found that
asymmetric flapping wing mechanism is suitable to obtain the net positive lift even at Zero
angle of attack.

CE 2.3.4 Identified issues and their solutions
2.3.4.1 Issues
There were some of the most significant issues in our project of Development of
Asymmetrical Flapping Mechanism for Flapping Wing MAV. The first technical issue that
occurred in our project was due to the complications in installation of the flapping wings
micro air vehicles. This was mainly because of gliding ratio in this vehicle. The highest speed
was not been undertaken in the project and hence was our project was suffering significant
technical faults or difficulties. Furthermore, our design did not have the ability to take the on
board television equipments. Due to this, the flying was not possible in the boundary layer of
the earth. The second issue that I had faced in this project was due to the asymmetrical
flapping mechanism for this flapping wing MAV. Since, the MAV was small and did not
have the ability to solve every control system with the combination of high maneuverable
aerodynamic configuration. All of these issues were becoming major problems for the project
and should have been resolved for the successful execution.
2.3.4.2 Solutions
I provided solutions to every problem faced in the project. My solutions were
extremely helpful for the project and thus all our issues were solved. For the first issue, I
provided the suggestion in exhibiting the proper forward flight capability such as specific
gliding ratio in order 8 and the highest speed in order of 20metres in one second. Moreover, I
also gave the suggestion that flight duration must be more than 1 hour and power loading
must be of 13KG per kilowatt. For the second important issue, I provided the solution of
carrying light weighted equipments of the television and hence our asymmetrical flapping
mechanism would be easily executed. The low maneuverable aerodynamic is considered as
more effective for the flapping wing micro air vehicle.

CE 2.3.5 Plan to produce creative and innovative work
We made a significant plan for our project. Our plan was to bring out creative and
innovative work by working mutually. We divided our work perfectly and every one carried
out their responsibility with utmost sincerity and perfection. Thus, our project was a
successful one.