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Design of Electrical Power Subsystem of a Low Orbit Satellite
Current Issue
Volume 6, 2019
Issue 3 (May)
Pages: 17-24   |   Vol. 6, No. 3, May 2019   |   Follow on         
Paper in PDF Downloads: 25   Since Sep. 26, 2019 Views: 229   Since Sep. 26, 2019
Authors
[1]
Abdullahi Ayegba, Mathson Research Centre, a Division Mathson Space International School, Karshi, Abuja, Nigeria.
[2]
Vincent Andrew Akpan, Department of Biomedical Technology, the Federal University of Technology, Akure, Nigeria.
[3]
Ale Felix, Department of Electrical & Electronics Engineering, University of Abuja, Gwagwalada, Nigeria.
Abstract
An electrical power subsystem of a satellite is the satellite subsystem responsible for the supply of energy to other subsystems of the satellite. The aim of this work is to design the electrical power subsystem for a low earth orbit which will orbit at 650 km altitude above the earth’s surface. The average power of the satellite is 800 W and it has a life span of 8 years. The design was done using direct energy transfer method and mathematical computation process to calculate various parameters of the power generation, storage, regulation and distribution units. The result showed that a total of 9647 cells, consisting of 254 cells in parallel and 38 series (string) cells and array mass of the solar array was 65.5 kg will be needed for the power generation unit while the power storage unit is made up of 28 batteries of 1.25 V battery voltage and 53 Ahr capacity. In addition, the charge controller of amperage, 64 A is used for the charge regulation of the batteries while the parameters for the power distribution unit (bulk converter) calculated accordingly.
Keywords
Battery, Bulk Converter, Energy, Orbital Period, Power Regulation Unit, Satellite
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