Design and Vibration Characteristics Analysis of ...

Design and Vibration Characteristics Analysis of Quadcopter Body Frame

Anamika Bhandari

M.Tech Student, Department of Mechanical Engineering,

Graphic Era University,

Dehradun, Uttrakhand, India.

Faraz Ahmad

Research Scholar, Department of Mechanical Engineering,



Pushpendra Kumar

Associate Professor, Department of Mechanical Engineering,



Pravin P. Patil

Professor, Department of Mechanical Engineering,



Abstract Quadcopter is a Mechatronics device consisting of mechanical

and electronic equipment. It consist four propellers which

provide thrust force to the Quadcopter. Furthermore, during

the Quadcopter flight body frame and other electronics

component are subjected to vibration. Present study discusses

the Modelling and vibration analysis of the Quadcopter body

frame to check the failure frequency range by changing the

boundary condition. The 3-D model of the Quadcopter body

frame was designed in Creo 2.0 and analysis was performed

on Ansys 16.2. The simulation result helps researcher's in

designing the Quadcopter frame for heavy transportation

application.

Keywords: Quadcopter, body frame, FEA, Vibration,

Deformation.

Introduction

A Quadcopter UAV is a device which is wildly used in the

transportation and photography now days. It has four

propellers driven by actuators and electronic component are

also mounted on the Quadcopter body frame [1]. The present

study deals with the body frame vibration analysis with

varying boundary conditions. Many researchers contribute in

improving the dynamics and strength of the Quadcopter for

batter flight accuracy. Following are some literature which

describes the previous work, done by the researcher.

Santosh kumar et.al [2] has analyzed the deformation, von

Misses stress for the various key components of multi mode

vehicle Quadcopter. Anudeep M [3] has performed

modification in the design of the Quadcopter centre plate and

the static analysis is performed to sustain the load generated in

the vehicle. By changing the base plate weight is reduced so

the power consumption is reduced and the deformations were

within the safe limit. vijay k. P. et.al [4] had studied the

comparison between the ss-1 and X type body frame of

Quadcopter. Furthermore, computational fluid dynamic and

structural analysis was performed, which shows that ss-1

frame was better than X-frame. Mass reduction in ss-1 frame

was more than X-frame which reduced the weight and the

material cost. Qiaoyu Zhang (2015) [5] has studied the three-

layered sandwiched structure of Quadcopter to lower the

weight and rotator inertia.

Endrowednes KUANTAMA et al. [6] have studied the frame

modelling of the Quadcopter to determine the stability of the

plastic based body frame. Body frame was designed in solid

work and analyzed by Finite Element Analysis (FEA). Pan

Wei et.al. [7] has presented the study to analyze the static

analysis on the frame in order to determine the various

importance of the FEA in frame design. First he designed the

suitable frame in ProE software, secondly choose the right

material which reduces the weight of the Quadcopter,

furthermore, and analyze the result in the ANSYS to

determine the strength and stiffness of the Quadcopter body

frame. S.P. Yeong et.al [8] has studied the Computational

Fluid Dynamics on propeller design to optimize the

aerodynamic performance without making changes on the

structural design. Mohd Khan (9) has presented the study on,

handling of Quadcopter with the angular precision by

adjusting the thrust with respect to the voltage supply. Jae-

Neung Lee et. al [10] has study the image processing of the

UAV in domestic and international trends .He had processed

the image by using SIFT(scale invariant features transform)

matching and explained the application for the aerial

surveillance for the public service disaster control.

Vishank Bhatia et al. [11] have presented the study on the

design optimization and the structural analysis of quadcopter

frame through the study of the response surface methodology.

Parameters used for the optimization included the Von Mises

stress and total deformation which concluded that the design is

safer than the original design validated by the drop –test.

Marco c.De Simone et al. [12] has studied the inverse

dynamics analysis for the feed forward thrust and PID

International Journal of Applied Engineering Research ISSN 0973-4562 Volume 14, Number 9, 2019 (Special Issue) © Research India Publications. http://www.ripublication.com

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controller for feedback control in presence of wind field by

analyzing the aerodynamic effect. Furthermore the study

concludes that 2D model will be used for the starting analysis

of a 3D model with the variation of the thrust coefficient.

Kalpesh N.Shah et al. [13] have presented the study on weight

lifting capacity of quadcopter. Static structural analysis is

performed with the stress of about 15.4 Mpa which is in the

limit. His main goal is to fabricate the quadcopter so that it can

be used in the multiple operations like military, traffic

monitoring and rescue operations. R Nallappan et al. [14] has

preformed the modal, static and the harmonic analysis on the

frame so as to sustatin the loads in order to determine small

deformation in the design of the quadcopter which could be

seen in the center of the plate that is under the safe condition.

The present study deals with the modeling and

vibration characteristics analysis of Quadcopter body frame

and the study was arranged in following section: Introduction,

Material properties and FEA simulation, FEA result of body

frame and, Conclusion.

Material properties and FEA simulation

CFRP (Carbon Fiber Reinforced Polymer) material is

generally use in military and aerospace application for its high

strength to weight ratio, high fatigue strength and good

corrosion resistance. The material has 1600 Kg/m of density,

0.3 Poisson’s ratio and 70000 Mpa of young modulus of

elasticity.

Body frame is a rigid construction of Quadcopter, which

contain the propeller arm and other controlling component.

The present Cad model of Quadcopter body frame was design

in Creo and analysis was performed by Ansys 16.2. Ansys

software reduces the number of prototypes that are to be run

while designing and optimizing. It improves the design quality

and productivity of designer [15]. Figure 1 and 2 shows the

cad model and mesh model of the Quadcopter body frame.

Figure 1: Cad model

Figure 2: Mesh model

Figure 3: fixed Propeller Arm

Figure 4: Fixed body base

FEA result of body frame

In present work the body frame was fixed by two different

positions to determine the most prone area of failure and the

failure frequency range. Figure 3 and 4 shows the fixed

boundary condition for fixed Propeller Arm and Fixed body

base respectively. The blue color shows the fixed position in

figure 3 and 4.


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Fixed Propeller Arm Quadcopter body frame result

Mode 1 (1084.5 Hz) Mode 2 (2607.6 Hz)

Mode 3 (2975.5 Hz) Mode 4 (3085.6 Hz)

Mode 5 (4395.3 Hz) Mode 6 (4412.9 Hz)

Figure 5: Vibration frequency mode for fixed propeller Arm

Fixed body Base Quadcopter body frame result

Mode 1 (1197.8Hz) Mode 2 (1203.2 Hz)


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Mode 3 (1204.2 Hz) Mode 4 (1205.4 Hz)

Mode 5 (1295.3 Hz) Mode 6 (1299.8 Hz)

Figure 6: Vibration frequency mode for fixed body Base of Quadcopter

The figure 5 and 6 shows the frequency variation on different

loading condition. We can see in figure 5 and 6 that the

maximum deformation takes place at the centre of the body

frame, and end point of propeller respectively. The maximum

deformation can be seen by the red colour and minimum by

blue. Natural frequency of fixed propeller arm varies from

1084.5 Hz to 4412.9Hz and 1197.8Hz to 1299.8 Hz for fixed

body Base. Table 2 shows the natural frequency and figure 7

shows the variation graph for both the boundary conditions.

Table 1: Natural frequency variation for Frame

No. Of

Mode

Fixed

Propeller

Arm

Fixed

Body

Base

1 1084.5 1197.8

2 2607.5 1203.2

3 2975.5 1204.2

4 3085.6 1205.4

5 4395.3 1295.3

6 4412.9 1299.8

Conclusion

The detailed study of the modal analysis has been carried out

by ansys workbench. Hence the regions more prone to failure

were determined by using fixed propeller arm and fixed body

base boundary conditions. Furthermore the frequency of

failure varies from 1084.5 Hz to 4412.9Hz for fixed propeller

arm and 1197.8Hz to 1299.8 Hz for fixed body base. From

table 1 and figure 7 we can see that fixed propeller arms has

lower frequency of failure than the fixed body base. So that

1084.5 Hz is the minimum fundamental frequency of failure

for the considered Quadcopter body frame.

Figure 7: frequency variation graph

Reference

[1] Ahmed, F., Kumar, P., & Patil, P. P. (2016). Modeling

and simulation of a quadcopter UAV. Nonlinear Studies,

23(4).

[2] S. Kumar, and P.C. Mishra, Finite element modeling for

structural strength of quadcoptor type multi mode

vehicle. Aerospace Science and Technology, 53, pp.252-

266 2016.

[3] M. Anudeep,G. Diwakar and R. Katukam, Design of A

Quad Copter and Fabrication. International Journal of


Page 69 of 70

Innovations in Engineering and Technology, ISSN,

pp.2319-1058,2014.

[4] P.Vijay Kumar,T.Shivam, computational fluid dynamics

and structural analysis of quadcopter frame ss-1 and

comparison with x-frame. Volume: 06 Issue: 01 , Jan-

2017.

[5] Q. Zhang,J. Chen, L.Yang,W. Dong, X.Sheng, andX.

Zhu, Structure optimization and implementation of a

lightweight sandwiched Quadcopter. In International

Conference on Intelligent Robotics and Applications (pp.

220-229). Springer, Cham, August 2015.

[6]E. Kuantama,d. Craciun. And r.tarca. Quadcopter Body

Frame Model and Analysis. Annals of The University of

Oradea, pp.71-74,2016.

[7] Wei, P., Yang, Z. and Wang, Q.(2015) “ The Design of

Quadcopter Frame Based On Finite Element

Analysis”,In 3rd International Conference on

Mechatronics, Robotics and Automation. Atlantis Press.

[8] Yeong, S.P. and Dol, S.S.(2016) “Aerodynamic

Optimization of Micro Aerial Vehicle” ,Journal of

Applied Fluid Mechanics, 9(5).

[9] Khan, M. (2014) “Quadcopter flight dynamics”,

International Journal of Science and Technology

Research, 130-135.

[10]Lee, N.J and Kwak, K.C .(2014) “A Trends Analysis of

Image Processing in Unmanned Aerial Vehicle”,

International Scholarly and Scientific Research &

Innovation 8(2).

[11]Bhatia, V., Karthikeyan, R., Ganesh Ram, R. K., &

Cooper, Y. N. (2014). Design Optimisation and Analysis

of a Quadrotor Arm using Finite Element Method. In

Applied Mechanics and Materials (Vol. 664, pp. 371-

375). Trans Tech Publications.

[12]De Simone, M. C., Russo, S., & Ruggiero, A. (2015).

Influence of Aerodynamics on Quadrotor Dynamics.

Recent Researches in Mechanical and Transportation

Systems Influence, 111-118.

[13]Shah, M.K.N., Dutt, M.B.J. and Modh, H.( 2014) “

Quadrotor–an unmanned aerial vehicle”, International

journal of Engineering development and research, 2(1),

pp.1299-1303

[14]R Nallappan, CasindraHellanMaxim, P BarathKumar.

(2016) “Design and Analysis of Quadcopter”.

International Conference on Systems, Science, Control,

Communication, Engineering and Technology: 248-252.

[15]Ahmad, F., Tomer, V., Kumar, A., & Patil, P. P. (2016).

FEA Simulation Based Thermo-mechanical Analysis of

Tractor Exhaust Manifold. In CAD/CAM, Robotics and

Factories of the Future (pp. 173-181). Springer, New

Delhi.


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