Trade-off analysis of low earth orbit spacecraft power supply system by Genetic algorithm

Mohamed, Ahmed Mokhtar; Amer, Fawzy ElTohamy H.; Mostafa, R.; Mahmoud, Ahmed A. Hakim

doi:10.1109/aero.2016.7500851

Cited by 7 publications

(2 citation statements)

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“…c. The efficiency of the satellite power subsystem will be roughly = 0.8 and = 0.9 where is the efficiency of the spacecraft power subsystem to supply the power from the array to the loads in daylight. However, is the efficiency of the spacecraft power subsystem to supply the power from the array to the batteries for charging during daylight and from the batteries to the loads during eclipse [3]. d. The degradation per year for the multi-junction solar cells, like the triple junction (3J) cells, is 0.5%.…”

Section: The Solar Array Designmentioning

confidence: 99%

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Design PV system for a small GEO satellite and studying the effect of using different types of propulsion

Lotfy

Anis

Halim

2019

IJAAS

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<p>This paper presents an optimum design of the solar Photo-Voltaic (PV) power system for small Geostationary Earth Orbit (GEO) satellites using triple junction solar cells and advanced Lithium Ion batteries. The paper applies the proposed system on various propulsion technologies; full chemical, full electrical and hybrid propulsions. This research work studies the capability to fulfil efficiently all the satellite power requirements during both the launching and the on-station phases while reducing the high cost challenge. Since the propulsion type is a key factor for the satellite cost, an economic analysis is demonstrated and investigated in two different strategies. The first scenario fixes the satellite weight and offers the revenue due to the increase in the satellite payload. However, the second scenario evaluates the saving profits due to the reduction in the satellite weight using the same number of satellite transponders. The analytical comparison among the different propulsion techniques shows the superior advantages of using the full electrical satellites. </p>

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Section: The Solar Array Designmentioning

confidence: 99%

“…b. Calculating the required output power at the beginning of life (BOL) of the satellite = cos = 315.78 Watt (3) where is the incidence angle between the vector normal to the solar array and the direction of the sun line. In the presented design, equals zero since the satellite uses a power tracking mechanism.…”

Section: The Solar Array Designmentioning

confidence: 99%