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Design of the structural arrangement for a space reflector via parametric and topology optimization
- Authors: Filina E.K.1,2, Golubev E.S.1,2, Mikhailovskiy K.V.1, Arkhipov M.Y.2
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Affiliations:
- Bauman Moscow State Technical University
- Lebedev Physical Institute of Russian Academy of Sciences
- Issue: Vol 20, No 4 (2019)
- Pages: 276-284
- Section: Aviation and rocket and space technology
- URL: https://journals.rudn.ru/engineering-researches/article/view/23420
- DOI: https://doi.org/10.22363/2312-8143-2019-20-4-276-284
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Abstract
Development of the optimal structural arrangement for a reflector with the aim to improve its mass and design is of importance due to the necessity to increase areal density and decrease rigidity of the modern space antennas vehicles. Currently, CAE-systems allow to design reflectors using both traditional methods, for example, parametric optimization, and methods which are innovative in this field, such as topology optimization. The paper compares two methods of the structural arrangement design for a thin dimensionally stable reflector operating as part of a geostationary spacecraft: parametric and topology optimization. The algorithms of the structural arrangement development which include the statement of the optimization problem, geometry design and a number of check analyses are presented. A number of structural of a space reflector design under the action of loads at the stage of launch, temperature gradients at the exploitation conditions and modal analysis is performed. The designed reflectors are compared. The studies performed allowed us to develop the optimal structural arrangement for a space reflector using the parametric and topology optimization. The optimal structural arrangement for a space reflector using the optimization could be produced surface figure error (estimated in RMS) with respect to the theoretical paraboloid.
About the authors
Elena K. Filina
Bauman Moscow State Technical University; Lebedev Physical Institute of Russian Academy of Sciences
Author for correspondence.
Email: konst_mi@mail.ru
post-graduate student of the Rocket-Space Composite Structures Department (SM13) at BMSTU, engineer at Astro Space Center of LPI RAS.
5 2-ya Baumanskaya St., bldg. 1, Moscow, 105005, Russian Federation; 84/32 Profsoyuznaya St., Moscow, 117997, Russian FederationEvgenii S. Golubev
Bauman Moscow State Technical University; Lebedev Physical Institute of Russian Academy of Sciences
Email: konst_mi@mail.ru
post-graduate student of the Technologies of Space-Rocket Mechanical Engineering Department (SM12) at BMSTU, lead engineer at Astro Space Center of LPI RAS.
5 2-ya Baumanskaya St., bldg. 1, Moscow, 105005, Russian Federation; 84/32 Profsoyuznaya St., Moscow, 117997, Russian FederationKonstantin V. Mikhailovskiy
Bauman Moscow State Technical University
Email: konst_mi@mail.ru
Associate Professor of the Rocket-Space Composite Structures Department (SM13) at BMSTU, PhD in Engineering Sciences
5 2-ya Baumanskaya St., bldg. 1, Moscow, 105005, Russian FederationMikhail Yu. Arkhipov
Lebedev Physical Institute of Russian Academy of Sciences
Email: konst_mi@mail.ru
senior researcher at Astro Space Center of LPI RAS, PhD in Engineering Sciences
84/32 Profsoyuznaya St., Moscow, 117997, Russian FederationReferences
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