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.
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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