The solar array is considered one of the famous and important primary power sources of a satellite. For solar array design, the required power and voltage level should be achieved to satisfy the requirements of the spacecraft Loads successfully. A case study for a real low earth orbit (LEO) satellite is developed to design and simulate a spacecraft solar array in orbit before manufacturing and also to predict the behavior of the designed spacecraft solar array system in order to analyze solar array performances in orbit under the whole operating conditions and degradation factors. The designed solar array is composed of one panel to provide the needed electric power during the space mission. The space mission specifications and power requirements are presented. In this paper, a complete mathematical model is constructed taking into account the whole degradation factors and environmental conditions until the end of life of the satellite, a thermal model is built for the solar array including the whole thermal effects on the solar array in orbit. MATLAB program is developed to calculate the whole design parameters and verifying the solar array design under the whole operating conditions and the environmental conditions by calculating the operating temperature and verifying that the required design parameters are achieved at this temperature. The results of the developed design of solar array computer program are validated by a real telemetry of the proposed satellite.
Verification of solar array design for low earth orbit spacecraft under worst case scenario
2018-03-01
1162626 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
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