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Power Supply Subsystem for Small Satellite Application
N. El-Gohary, T. El-Shater, M.M. Sakr, A.A. Mahfouz
Maximum Power Point Tracking, Small Satellites, Direct Energy Transfer, Flywheel Energy Storage System, Space Vector Pulse Width Modulation
Subtopic: PV System Reliability and Availability
Event: 28th European Photovoltaic Solar Energy Conference and Exhibition
Session: 5BV.4.64
4036 - 4040
ISBN: 3-936338-33-7
Paper DOI: 10.4229/28thEUPVSEC2013-5BV.4.64
0,00 EUR
Document(s): paper, poster


Space mission analysis and design begins with one or more broad objectives and constraints and then proceeds to define a space system that will meet them at the lowest possible cost. The satellite mission under study is imaging the Egyptian land or any other places on earth and sending these images to the data receiving station. Satellite power supply system has the responsibility of providing continuous, regulated and conditioned power to payloads (multiband earth imager and middle infrared earth imager camera) and other subsystems during all mission phases. Satellite primary source of power depends upon the space mission duration. The duration of remote sensing satellite mission is from five to seven years. Increasing the satellite lifetime from five years to fifteen years will reduce satellite designing and launching costs. So a high efficiency and long lifetime satellite power supply subsystem using a tipplejunction solar cell of 29.5% efficiency controlled by maximum power point tracking and FWESS as a secondary power source. This system is compared to another one used in the Egyptian satellite EgyptSat-1 using direct energy transfer (DET) technique, shunt regulator , and CB as a secondary power source.