الفهرس 
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Abstract
This thesis is focused on the designing of the PPSS. In this work the designed system is based on the conversion of PV energy into electric power via the (PV effect) using the solar cells. The main goal of the design procedure of the spacecraft (PPSS) is the verification of the optimal solution of generating the electric power required for the spacecraft loads, during the daylight of the orbit, and also able to charge the battery (SPSS) with the required power for the spacecraft loads, during the eclipse period of the orbit.
This thesis introduces a model of (PV) module for space application. So the implemented module simulates the electrical performance of the PV system in space application, and it executed in Simulink / MATLAB environment. It is validated using real requirements of space mission, with real space photovoltaic cell characteristics. The fundamental equations of the PV cell were utilized with taking in consideration the impacts of space radiation and the variation of the operating temperature of the cell. The P-V and I-V characteristics of PV module are presented as a function of space operating temperature and the space radiation.
The model is utilized to implement a complete space photovoltaic system for space applications and simulate its behaviour. And it can compare between the several categories of PV cells using a real mission requirement of a satellite platform.
Finally this model presents the relationship between space photovoltaic module parameters and its performance, and it achieves the nonlinearity between the current and voltage characteristics and the power and voltage characteristics of the space photovoltaic module, the results of the simulation model are compared with the manufacturer’s published data and the limiting error is less than 5.9% for the whole voltage range.