Hostname: page-component-cd9895bd7-dk4vv Total loading time: 0 Render date: 2024-12-31T15:14:41.344Z Has data issue: false hasContentIssue false
  • English
  • Français

Design and implementation of a power distribution system adopting overcurrent protection

Published online by Cambridge University Press:  15 July 2020

M. Bekhti Open the ORCID record for M. Bekhti [Opens in a new window] ,
M. Bensaada  and
M. Beldjehem
M. Bekhti*
Affiliation:
Algerian Space Agency, Centre for Satellites Development, Research Department in Space Instrumentation, Oran, Algeria
M. Bensaada
Affiliation:
Algerian Space Agency, Centre for Satellites Development, Research Department in Space Instrumentation, Oran, Algeria
M. Beldjehem
Affiliation:
Algerian Space Agency, Centre for Satellites Development, Research Department in Space Instrumentation, Oran, Algeria
*
[email protected]
Get access Rights & Permissions [Opens in a new window]

Abstract

One of the most critical aspects of a small satellite is the electrical power system (EPS) since the electrical power is necessary for the satellite to operate correctly during its predefined lifetime. The electrical power system consists mainly of solar cells, batteries, voltage converters and protection circuits. The electrical power system is responsible of providing stable power to the rest of the satellite subsystems.

In satellite electrical power systems, overcurrent protection is now becoming an important function handled by the power distribution module (PDM). This paper proposes a method to evaluate the suggested protection. With the proposed procedure we should be able to verify that every possible failure does not travel through the EPS and cause a fatal degradation of the electrical power system. This will allow a complete evaluation of functionality of the protection hardware.

This paper discusses the design and implementation of the power distribution module (PDM) for the coming generation of small satellites for the Algerian Space Agency (ASAL). The design must provide a reliable protection for the subsystems from the overcurrent associated with a device failure.

Keywords

Power systemsmall satellitesbipolar junction transistor (BJT) switchfield effect transistor (FET) switchhard wire switchfusesresettable fusespower distribution module
Type
Research Article
Information
The Aeronautical Journal , Volume 124 , Issue 1281 , November 2020 , pp. 1789 - 1797
Copyright
© The Author(s), 2020. Published by Cambridge University Press on behalf of Royal Aeronautical Society

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

REFERENCES

Ismail, M.N., Bakry, A., Selim, H.H. and Shehata, M.H.Eclipse intervals for satellites in circular orbit under the effects of earth’s oblateness and solar radiation pressure, NRIAG J Astron Geophys, 2015, 4, (1), pp. 117–122. https://doi.org/10.1016/j.nrjag.2015.06.001CrossRefGoogle Scholar
Slowikowski, J.Z. and Blewett, M.J.Power supplies, conditioning and distribution on UOSAT, Radio Electron Eng, 1982, 52, (819), pp. 425–430.CrossRefGoogle Scholar
Wong, H.S. and Blewett, M.J.The UoSAT-2 spacecraft power system, J IERE, 1987, 57, (5), pp. S.116–S.122.Google Scholar
OSullivan, D.Satellite power system topologies, ESA J, 1989, 13, (2), pp. 77–88.Google Scholar
Grasselli, U., Schirone, L. and de Luca, A. Overcurrent Protection Performance Evaluation, Space Power, Proceedings of the Sixth European Conference held 6-10 May, 2002 in Porto, Portugal. Edited by A. Wilson. European Space Agency, ESA SP-502, 2002, p.411, ESA SP.502.411G, 2002.Google Scholar
Jiang, Z., Dougal, R.A. and Liu, S.Application of VTB in design and testing of satellite electrical power systems, J Pow Sources, 2003, 122, pp. 95–108.CrossRefGoogle Scholar
Orlu, U., Yuksel, G., Gomes, L.M. and Hall, K. Bilsat-1: power system sizing and design, RAST 2003 (recent advances in space technologies), November 20–22, Istanbul, Turkey, 2003.CrossRefGoogle Scholar
Bekhti, M. and Sweeting, M.N.Power system design and in orbit performance of Algeria’s first micro satellite Alsat-1, Electric Pow Syst Res, 2008, 78, pp. 1175–1180.CrossRefGoogle Scholar
Calvente, J., Martinez-Salamero, L., Garces, P., Leyva, R. and Capel, A.Dynamic Optimization of Bidirectional Topologies for Battery Charge/Discharge in Satellites, IEEE Trans Pow Electron, 2011, 26, (9), pp. 1994–1999.Google Scholar
Madhusudhana, C.S. and Kishore, J.K. Optimum Power Control and Management (PCM) of Small Satellites for LEO and GEO applications, National Conference on Recent Developments in Electronics, India, Jan 18–20, 2013.Google Scholar
Bekhti, M.Design and Qualification Tests of the Alsat-1 High Efficiency Solar Panels, Int J Renew Energy Res, 2013, 3, (1), pp. 1–7.Google Scholar
Madhusudhana, C.S. and Kishore, J.K. Performance metrics for evaluating spacecraft Power Control and management (PCM), IEEE International Conference on Power Energy and Control, February 6–8, INDIA, 2013.CrossRefGoogle Scholar
UoSAT Engineering Research Unit, UoSAT Spacecraft data Booklet, Dept. of Electronic and Electrical Engineering University of Surrey, 1987, Guildford, UK.Google Scholar
Van der Zel, V.M. Autonomous power system for low earth orbit microsatellite, MSc Thesis, Guildford, UK, University of Surrey, 1990.Google Scholar
Patel, M.R.Spacecraft power systems, Associate Professor of Engineering, U.S. Merchant Marine Academy, Kings Point, New York, 2005.Google Scholar
Mohan, N., Undeland, T.M. and Robbins, W.P.Power Electronics: Converters, Applications, and Design, 3rd Edition, ISBN: 978-0-471-22693-2.Google Scholar