Methodology for calculating the de-weighting system of large-sized transformable elements of space vehicles for ground tests

Автор: Belyaev A. S., Filipas A. A., Tsavnin A. V., Tyryshkin A. V.

Журнал: Siberian Aerospace Journal @vestnik-sibsau-en

Рубрика: Aviation and spacecraft engineering

Статья в выпуске: 1 vol.22, 2021 года.

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This paper considers the methodology for calculating the de-weighting system of spacecraft elements for ground tests, taking into account the deployment options, de-weighting conditions, types and options of de-weighting systems. An example of calculation for a 3-section solar battery without a beam with incomplete de-weighting and with minimization of moments in the hinges is given. Genetic algorithms are used as an algorithm for determining the parameters of the de-weighting system, which allows obtaining the minimum moments in the hinges. The moments and forces acting in the system were checked by plotting diagrams in the expanded state. In addition, a check for compliance with the specified distance, based on design constraints, between the points of application of the weighting forces was made.

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Deweighting, spacecraft, testing in ground conditions, automatic control systems, parametric uncertainty.

Короткий адрес: https://sciup.org/148321791

IDR: 148321791   |   DOI: 10.31772/2712-8970-2021-22-1-106-120

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