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Modular design of electrical power subsystem for a remote sensing satellite
Author(s): Ehsan Kosari; Sajjad Ghazanfarinia; Mahboobeh Hosseingholi; Javad Haghshenas
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Paper Abstract

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

Paper Details

Date Published: 29 September 2017
PDF: 10 pages
Proc. SPIE 10423, Sensors, Systems, and Next-Generation Satellites XXI, 1042328 (29 September 2017); doi: 10.1117/12.2280023
Show Author Affiliations
Ehsan Kosari, Satellite Research Institute (Iran, Islamic Republic of)
Sajjad Ghazanfarinia, Satellite Research Institute (Iran, Islamic Republic of)
Mahboobeh Hosseingholi, Material and Energy Research Ctr. (Iran, Islamic Republic of)
Javad Haghshenas, Satellite Research Institute (Iran, Islamic Republic of)


Published in SPIE Proceedings Vol. 10423:
Sensors, Systems, and Next-Generation Satellites XXI
Steven P. Neeck; Jean-Loup Bézy; Toshiyoshi Kimura, Editor(s)

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