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Power Supply is one of the most important subjects in Remote Sensing satellite. Having an appropriate and adequate
power resources, A Remote Sensing satellite may utilize more complex Payloads and also make them more operable in
orbit and mission timeline. This paper is deals with a design of electrical power supply subsystem (EPS) of a
hypothetical satellite with remote sensing mission in Low Earth Orbits, without any restriction on the type and number of
Payloads and only assuming a constraint on the total power consumption of them. EPS design is in a way that can supply
the platform consumption to support Mission and Payload(s) requirements beside the power consumption of the
payload(s). The design is also modular, as it can be used not only for the hypothetical system, but also for the other
systems with similar architecture and even more needs on power and differences in some specifications. Therefore, a
modularity scope is assumed in design of this subsystem, in order to support the satellite in the circular orbits with
altitude of 500 to 700 km and inclination of 98 degrees, a sun-synchronous orbit, where one can say the design is
applicable to a large range of remote sensing satellites. Design process will be started by high level and system
requirements analysis, continued by choosing the best approach for design and implementation based on system
specification and mission. After EPS sizing, the specifications of elements are defined to get the performance needed
during operation phases; the blocks and sub-blocks are introduced and details of their design and performance analysis
are presented; and the modularity is verified using calculations for the confined area based on design parameters and
evaluated by STK software analysis results. All of the process is coded in MATLAB software and comprehensive graphs
are generated to demonstrate the capabilities and performance. The code and graphs are developed in such a way to
completely review the design procedure and system efficiency in worst case of power consumption scenario at the
beginning and end of satellite life
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