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In the current modern era, artificial satellites are considered as one of the greatest mankind creations. Satellites are used for several services and applications like remote sensing and earth observation services, meteorological and navigation services, search and rescue operations in addition to the space telescopes and the military purposes.
Satellite orbits are greatly varying, depending on the required mission of the satellite, and they are classified into a number of ways. In this thesis, the designed PV system will be applied on Geostationary Earth Orbit (GEO) satellites and small satellites like CubeSat.
Satellites are usually constructed from semi-independent computer-controlled subsystems, which attend many tasks such as power generation, thermal control, telemetry and command, attitude control and orbital control.
The power generation source is always one of the most sensitive and complicated issues in the field of satellite science due to several issues:
• The challenge of the area limitation constraints for the solar panels versus the required power capacity forces the satellite technology to develop solar cells with high efficiencies.
• High advanced technology for batteries is required to efficiently supply the satellite subsystems during the periodic eclipse durations. This is, in addition to fulfill the requirement of batteries long lifetime due to the impossibility of their replacement and maintenance.
• The cost of the main components is very high, which lead to many theoretical and technical researches for decreasing the financial budget while preserving the same technical requirements.
Design for the satellite solar arrays will be presented and discussed with several technical considerations. The thesis consists of five chapters including lists of contents, figures, and tables as well as a list of references.
Chapter 1: contains a thesis introduction, as well as literature review, covering satellite types and their applications.
Chapter 2: discusses satellites size, altitude classifications, defining the satellite orbital period.
Chapter 3: discusses Design of an Optimum PV System for the GEO Satellites, small GEO and the impact of the types of propulsion on the sizing of a solar array. Identifying the optimum solar cell type to fit with the available solar panels area and the power demands for CubeSat.
Calculating the optimum sizing of the battery bank storage and selecting the type of batteries that copes.
Chapter 4: discusses the economic analysis of the effect of various types of propulsion on solar array and thus reduces the weight of the satellite, an economic analysis is demonstrated and investigated in two different plans. The first option fixes the satellite weight and offers the revenue due to the increase in the satellite payload. However, the second option evaluates the saving profits due to the reduction in the satellite weight using the same number of satellite transponders
Chapter 5: contains conclusions and recommended for future work.