Abstract
The preliminary design of geostationary communication satellite solar array is presented in this work. Based on the power requirements, power margin requirements and performance requirements, the number of panels, strings and cells to be used on the solar array were defined. The main objective of this study was to optimize the power generated from the satellite solar array and the extraction of the parameters of a photovoltaic module, which is subject to the space environment and under a series of practical constraints, in order to extract the desired performance parameters for multiobjective functions, taking into account the solstice and equinox periods during temperature operation. A gravitational search algorithm based on the law of gravity and mass interactions was introduced. This algorithm has proved its effectiveness in optimizing system parameters in the literature. From the results obtained in this work, the total power of the optimized system was reduced by 181 W. The degradation and output power characteristics of the solar panels were calculated for different temperature values.
Highlights
The growing demand for satellite communications with high subsystems reliability and the increasing complexity of satellite power subsystems that use large deployable solar panels and appropriate electronics modules, with increasing embedded satellite payloads, are needs that make a difficult task even more difficult
Several simulations and analytical calculations have been performed to determine the optimal parameters of the geostationary satellite solar array
In order to determine the number of cells in parallel and in series, the number of the solar panel sections, and the number of panels needed in the solar array, numerous aspects must take into account the power of the satellite at end of life as well as the various degradation factors caused by the space environment
Summary
The growing demand for satellite communications with high subsystems reliability and the increasing complexity of satellite power subsystems that use large deployable solar panels and appropriate electronics modules, with increasing embedded satellite payloads, are needs that make a difficult task even more difficult. One of the important requirements in each space mission is the design of a system to provide uninterruptible energy with desired quality and quantity. The satellite power subsystem project must satisfy its demand for electricity during the mission. To obtain this electrical energy, it is necessary to calculate the required area of the satellite structure for the installation of solar panels. The design of a solar array on a specific space mission is based on the mission requirements. Solar cells are still the most suitable energy source in space missions. The behavior of solar cells is strongly related to environmental conditions (Castañer and Silvestre 2002; Luque and Hegedus 2003)
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