Design and Development of Quadcopter’s Frame

  • Kaspul Anuar Mechanical Engineering, Universitas Riau, Indonesia
  • Anita Susilawati Mechanical Engineering, Universitas Riau, Indonesia
  • Syafri Syafri Mechanical Engineering, Universitas Riau, Indonesia
  • Warman Fatra Mechanical Engineering, Universitas Riau, Indonesia
  • Feblil Huda Mechanical Engineering, Universitas Riau, Indonesia
  • Nazaruddin Nazaruddin Mechanical Engineering, Universitas Riau, Indonesia
  • Dedi Rosa Putra Cupu Mechanical Engineering, Universitas Riau, Indonesia
DOI: http://dx.doi.org/10.36842/jomase.v68i1.360

Abstract

The purpose of this research is to obtain a design and prototype of quadcopter’s frame, which be developed further as a quadcopter that capable of carrying payload of 1.5 kg with flight time of more than 20 minutes. The design begins with estimating the values of Maximum Take-Off Weight (MTOW), required thrust, propeller dimensions, and wheelbase dimensions of the quadcopter. The results show the MTOW of the quadcopter was 5 kg, with each motor requiring of 2.5 kg of thrust per arm. The wheelbase dimension was 790 mm, and the propeller diameter of 17 inches. A wheelbase dimension was utilized to develop three conceptual frame designs for the quadcopter. The three conceptual designs were selected using a decision matrix table. The selected design was calculated for its structural strength by applying a load of 2.5 kg on each motor mounting. The results show the maximum stress value of 21.17 MPa, the maximum deflection of 3.5 mm, and safety factor of 22.44. Then, the prototype of quadcopter’s frame was manufactured. Therefore, the producing of prototype was measured the mass and deflection. Based on the measurements conducted, the quadcopter frame has an actual mass of 595 grams and a maximum deflection of 3.7 mm. The actual deflection value and the actual mass are close to the deflection and mass obtained from the calculation.

##Keywords:## Quadcopter Frame, Structural Strength, Maximum Stress.
Published
Mar 30, 2024
How to Cite
ANUAR, Kaspul et al. Design and Development of Quadcopter’s Frame. Journal of Ocean, Mechanical and Aerospace -science and engineering-, [S.l.], v. 68, n. 1, p. 33-39, mar. 2024. ISSN 2527-6085. Available at: <https://isomase.org/Journals/index.php/jomase/article/view/360>. Date accessed: 19 aug. 2024. doi: http://dx.doi.org/10.36842/jomase.v68i1.360.
Citation Formats
Issue
Vol 68 No 1 (2024): Journal of Ocean, Mechanical and Aerospace -science and engineering- (JOMAse)
Section
Articles

References

[1] Tyan, M., Van Nguyen, N., Kim, S., & Lee, J. W. (2017). Comprehensive preliminary sizing/resizing method for a fixed wing–VTOL electric UAV. Aerospace Science and Technology, 71, 30-41. doi: 10.1016/j.ast.2017.09.008.
[2] Asral, Kaspul Anuar, & Agung Soegihin. (2022). Aerodynamic Analysis of Unnamed Aerial Vehicle Serindit V-2 Using Computational Fluid Dynamics. Journal of Advanced Research in Fluid Mechanics and Thermal Sciences, 93(1), 83–93. https://doi.org/10.37934/arfmts.93.1.8393
[3] Golui, D.K., Pradhan, N., Tudu, S.M. & Anjumol, K.S. (2019). Detailed Design of a Tail-Sitter. Report Project, 1-76, Depart. of Aerospace Engineering Indian Institute of Space Science and Technology Thiruvananthapuram. doi: 10.13140/RG.2.2.10704.87045.
[4] Anuar, K., Fatra, W. & Akbar, M. (2020). Tricopter vehicle frame structure design integrated as platform of fixed wing atha mapper 2150. Journal of Ocean, Mechanical and Aerospace -Science and Engineering-, 64(2), 68-72. doi:10.36842/jomase.v64i2.218.
[5] Anuar, K., Fatra, W., Akbar, M., Nazaruddin, N., Syafri, S., Sari, A.W., & Utama, R.R. (2023). Design and aerodynamic analysis of fixed-wing vertical take-off landing (fw-vtol) uav. Journal of Advanced Research in Fluid Mechanics and Thermal Sciences, 106(1), 136-146.
[6] Jetley, P., Sujit, P. B. & Saripalli, S. (2017). Safe landing of fixed wing UAVs. In 2017 47th Annual IEEE/IFIP International Conference on Dependable Systems and Networks Workshops (DSN-W), 2-9), IEEE. doi: 10.1109/DSN-W.2017.43.
[7] Anuar, K. & Herisiswanto (2019). Desain perangkat hight lift device (hld) guna meningkatkan koefisien gaya angkat pada sayap wahana terbang uav serindit v-1. Multitek Indonesia, 13(1), 9-15. doi: 10.24269/mtkind.v13i1.1736
[8] Avanzini, G., Di Nisio, A., Lanzolla, A.M.L. & Stigliano, D. (2020). A test-bench for battery-motor-propeller assemblies designed for multirotor vehicles. In 2020 IEEE 7th International Workshop on Metrology for AeroSpace (MetroAeroSpace), 600-605). IEEE. doi: 10.1109/MetroAeroSpace48742.2020.9160320.
[9] Anuar, K. & Akbar, M. (2019). Wing design of uav serindit v-1. In IOP Conference Series: Materials Science and Engineering, 539(1), 012002. IOP Publishing. doi: 10.1088/1757-899X/539/1/012002.
[10] Yu, S. & Kwon, Y. (2017). Development of VTOL drone for stable transit flight. Journal of Computer and Communications, 5(7), 36-43. doi: 10.4236/jcc.2017.57004.
[11] Anuar, K., Akbar, M., Aziz, H.A., & Soegihin, A. (2022). Experimental test on aerodynamic performance of propeller and its effect on the flight performance of serindit v-2 uav. Journal of Advanced Research in Fluid Mechanics and Thermal Sciences, 91(2), 120-132. doi: 10.37934/arfmts.91.2.120132.
[12] Das, H., Baskaran, V. & Arya, H. (2016). Static performance analysis of electric propulsion system in quadrotors. In 2016 International Conference on Control, Instrumentation, Communication and Computational Technologies (ICCICCT), 495-500). IEEE. doi: 10.1109/ICCICCT.2016.7988001.
[13] Mohammed, M.G., Messerman, A.F., Mayhan, B.D. & Trauth, K.M. (2016). Theory and practice of the hydrodynamic redesign of artificial hellbender habitat. Herpetological Review, 47(4), 586-591.
[14] Hibbeler, R.C. (2011). Mechanics of Materials, Eight Edd, Prentice Hall.
[15] Teguh, M.T., Anuar, K., Taslim, M. & Saputra, R.G. (2019). The application of empty palm fruit bunch (epfb) as a material for fixed wing type unmanned aerial vehicle fuselage production. Journal of Ocean, Mechanical and Aerospace-science and engineering-, 63(3), 13-16. doi: 10.36842/jomase.v63i3.133.