Resonant solar cell energy converter in the power supply system for small spacecraft

Zhuravlev, I. M.; V., Osipov, Alexander

doi:10.21293/1818-0442-2020-23-3-81-85

Cited by 1 publication

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“…Таким образом, оценку энергетических, надежностных и массогабаритных показателей ЭПА КА необходимо проводить постфактум (руководствуясь требованиями ТЗ по надежности). Несмотря на высокие показатели КПД оригинальных схем[2, 8], резервирование транзисторов внутри канала преобразования энергии на КЗ/обрыв приводит к резкому падению K УМ ЭПА. Введение резервирования отказа элемента на КЗ/обрыв за счет дополнительного где N транз_общ -общее количество транзисторов в ЭПА, шт; N кан -общее количество каналов преобразования энергии в ЭПА, включая резервные, шт; N транз_осн -количество основных транзисторов в одном канале преобразования энергии, шт; N транз_рез -количество резервных транзисторов в одном канале преобразования энергии, шт; N отк -количество отказов, при которых должны обеспечиваться заданные характеристики электропитания; N транз_кан -общее количество транзисторов в одном канале преобразования энергии, шт.Приведенная формула демонстрирует, что при одинаковом количестве каналов преобразователя количество транзисторов в инверторно-трансформаторных преобразователях будет в 8 раз больше.…”

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Complex Designing Algorithm for Spacecraft Energy-Converting Equipment

Zhuravlev,

Lysenko,

Khlystunov

et al. 2023

Vestn. Čuv. univ.

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Introduction. The complication of the spacecraft payload requires the use of non-standard circuits. The analysis of scientific and technical publications shows that there is no formalized methodology for spacecraft energy-converting equipment designing. Reviewed publications consider some design algorithms taking into account one (efficiency) or two criteria (efficiency, weight and size characteristics). At the same time, the issues of ensuring trouble-free operation of energy-converting equipment are not sufficiently considered which leads to rejection of most part of proposed circuitsolutions and reduces developer efficiency. The research purpose is to form a spacecraft energy–converting equipment designing algorithm, taking into account the reliability, efficiency and relative power coefficient requirements. Materials and methods. The main provisions of the electrical circuit theory and the theory of technical systems reliability were used. All calculations were carried out in Mathcad 15.0. Research results. The article step-by-step discusses the design process using the example of boost and buck voltage converters. It is shown that taking into account the reliability requirements leads to a decrease of weight and size indicators (due to the additional mass of redundant elements) and efficiency (due to power losses on redundant elements). Converters with an AC-current node based on a double active bridge (active front end bridge inverter) and add-voltage circuits are considered. It can be seen that the use of converters with AC-current node in spacecraft energy-converting equipment is complicated because of low reliability or high weight and size meters. Conclusions. A converter circuit must ensure operation in the event of a single failure of a random power element. At the same time, scheme with a minimum number of power elements have the greatest prospects for application. A converter energy characteristic must be evaluated after ensuring the reliability.

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