Single Cell Li-Ion Polymer Battery Charge and Discharge Characterizations for Application on Solar-Powered Unmanned Aerial Vehicle

Parvathy Rajendran; Nurul Musfirah Mazlan; Howard Smith

doi:10.4028/www.scientific.net/KEM.728.428

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Single Cell Li-Ion Polymer Battery Charge and Discharge Characterizations for Application on Solar-Powered Unmanned Aerial Vehicle
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HomeKey Engineering MaterialsKey Engineering Materials Vol. 728Single Cell Li-Ion Polymer Battery Charge and...

Single Cell Li-Ion Polymer Battery Charge and Discharge Characterizations for Application on Solar-Powered Unmanned Aerial Vehicle

Abstract:

Solar-powered UAV is an alternative way to achieve high endurance and long range UAV flight. However, solar irradiance is not always available during the flight. Thus, secondary power source which is electrical batteries will improve the performance of solar-powered UAV when solar irradiance is not available. Therefore, bench test for LiPo battery is conducted in this paper for the design of solar-powered UAV power system. The impact of operating temperature at various charging and discharging rate on the duration to full charge and discharge and capacity level of a single LiPo battery were assessed. The solar module installed in solar-powered UAV developed by Aircraft Design Group, Cranfield University has to be designed to charge the battery pack at a nominal or maximum rate of 0.129 C and 0.155 C correspondingly. The solar module requires roughly 5.73 hours on nominal charging rate on 30 °C operating temperature to fully charge capacity level instead of 5.54 hours theoretical predicted. The battery pack will then discharge at cruise flight roughly about 0.071 C to a maximum of 1.685 C if required. If the battery pack is not charged, during cruise flight the battery capacity will deplete completely at about 6.51 hours for the same operating temperature, in contrast to the 6.48 hours based on the theoretical prediction. In addition, the usage of LiPo batteries for operation at high altitudes and/or extreme temperatures without an additional heating or cooling system for these battery packs is not favorable. Thus, it is best to charge at low charging rate and high operating temperature to store and utilize the most capacity from this battery.

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Periodical:

Key Engineering Materials (Volume 728)

Pages:

428-433

DOI:

https://doi.org/10.4028/www.scientific.net/KEM.728.428

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Online since:

January 2017

Authors:

Parvathy Rajendran, Nurul Musfirah Mazlan*, Howard Smith

Keywords:

Battery Testing, Cumulative Current, LiPo, LiPo Capacity, Solar-Powered UAV, UAV

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References

[1] X.F. Zhu, Z. Guo, Z.X. Hou, Solar-powered airplanes: A historical perspective and future challenges, Progress in Aerospace Sciences, 71 (2014) 36–53.

DOI: 10.1016/j.paerosci.2014.06.003

Google Scholar

[2] V. De Devabhaktuni, M. Alam, S.S.S.R. Depuru, R.C. Green, D. Nims, C. Near, Solar energy: Trends and enabling technologies, Renewable and Sustainable Energy Reviews, 19 (2013) 555-564.

DOI: 10.1016/j.rser.2012.11.024

Google Scholar

[3] H. Smith, P. Rajendran, Review of the Elementary Aspect of Small Solar-powered Electric Unmanned Aerial Vehicles, Aust. J. Basic & Appl. Sci., 8 (2014) 252-259.

Google Scholar

[4] S.G. Kontogiannis, J.A. Ekaterinaris, Design, performance evaluation and optimization of a UAV, Aerospace Science and Technology, 29 (2013) 339-350.

DOI: 10.1016/j.ast.2013.04.005

Google Scholar

[5] A. Chaves, A. T. Bahill, Comparison of Risk Analysis Approaches and a Case Study of the Risk of Incorporating Solar Photovoltaic Systems into a Commercial Electric Power Grid, Systems Engineering, 17 (2014) 89-111.

DOI: 10.1002/sys.21254

Google Scholar

[6] P. Rajendran, H. Smith, The development of a Small Solar Powered Electric Unmanned Aerial Vehicle Systems, Applied Mechanics and Materials, 465-466 (2014) 345-351.

DOI: 10.4028/www.scientific.net/amm.465-466.345

Google Scholar

[7] S. Jashnani, T.R. Nada, M. Ishfaq, A. Khamker, P. Shaholia, Sizing and preliminary hardware testing of solar powered UAV, The Egyptian Journal of Remote Sensing and Space Sciences, 16 (2015) 189-198.

DOI: 10.1016/j.ejrs.2013.05.002

Google Scholar

[8] P. Rajendran, H. Smith, Review of Solar and Battery Power System Development for Solar-Powered Electric Unmanned Aerial Vehicles, Advanced Materials Research, 1125 (2015) 641-647.

DOI: 10.4028/www.scientific.net/amr.1125.641

Google Scholar

[9] X.Z. Gao, Z.X. Hou, Z. Guo, R.F. J.X. Liu, X.Q. Chen, Energy management strategy for solar-powered high-altitude long-endurance aircraft, Energy Conversion and Management, 70 (2013) 20-30.

DOI: 10.1016/j.enconman.2013.01.007

Google Scholar

[10] F. Fazelpour, M. Vafaeipour, O. Rahbari, R. Shirmohammadi, Considerable parameters of using PV cells for solar-powered aircrafts, Renewable and Sustainable Energy Reviews, 22 (2013) 81-91.

DOI: 10.1016/j.rser.2013.01.016

Google Scholar

[11] P. Rajendran, H. Smith, Implications of longitude and latitude on the size of solar-powered UAV, Energy Conversion Management, 98 (2015) 107–114.

DOI: 10.1016/j.enconman.2015.03.110

Google Scholar

[12] X.Z. Gao, Z.X. Hou, Z. Guo, R.F. Fan, X.Q. Chen, The equivalence of gravitational potential and rechargeable battery for high-altitude long-endurance solar-powered aircraft on energy storage, Energy Conversion and Management, 76 (2013) 986-995.

DOI: 10.1016/j.enconman.2013.08.023

Google Scholar