Email this article Parametric analysis of the anisogrid body of the spacecraft for cleaning the orbit of space debris
- Authors: Belonovskaya I.D.1, Kolga V.V.2, Yarkov I.S.3, Yarkova E.A.3
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Affiliations:
- Orenburg State University
- Reshetnev Siberian State University of Science and Technology
- JSC Academician M. F. Reshetnev “Information Satellite Systems”
- Issue: Vol 22, No 1 (2021)
- Pages: 94-105
- Section: Section 2. Aviation and Space Technology
- URL: https://journals.eco-vector.com/2712-8970/article/view/562827
- DOI: https://doi.org/10.31772/2712-8970-2021-22-1-94-105
- ID: 562827
Cite item
Abstract
The article presents an approach to solving the problem of designing a spacecraft for cleaning the orbit of space debris (space garbage collector-KSM), the body of which is made in the form of a cylindrical mesh anisogrid shell. The design task is to select the optimal parameters of the anisogrid body of the KSM (the shape and cross-sectional area of the ribs, the number of annular and spiral ribs, material characteristics, etc.) that provide the necessary strength and stability of the structure with minimal weight. During the design process, a parametric analysis of the anisogrid housing of the space garbage collector was carried out. By varying the number and angle of inclination of unidirectional spiral ribs, we find the optimal design scheme that satisfies the specified safety and stability coefficients. Parametric analysis of the KSM body includes modeling of the main weight and strength parameters: determination of the stress-strain state of the structure, values of the body’s natural frequencies, determination of the bending margin from the longitudinal force, determination of the body mass.
The analysis of the load-bearing capacity of the anisogrid housing of the space garbage collector was carried out by the finite element method using the MSC Nastran software package. A finite element mesh model was created from a two-node spatial finite element bundle. The disk attached to the end of the shell was modeled using a rigid finite element. The size of the final beam element for all shell models was the same and equal to 10 mm.
During the parametric analysis, three variants of the mesh composite structure with a different number and angle of inclination of unidirectional spiral ribs were considered.
Based on the results of parametric analysis of the spacecraft body, its geometric dimensions are determined and the mass of the spacecraft structure as a whole is minimized.
About the authors
Izabella D. Belonovskaya
Orenburg State University
Email: t251589@mail.ru
Dr. Sc., Professor, Professor of the Department of Mechanical Engineering Technology, Metalworking Machines and Complexes
Russian Federation, 13, Pobedy Av., Orenburg, 460018Vadim V. Kolga
Reshetnev Siberian State University of Science and Technology
Author for correspondence.
Email: kolgavv@yandex.ru
Dr. Sc., Professor, Professor of Department of Aircraft
Russian Federation, 31, Krasnoiarskii Rabochi Prospekt, Krasnoyarsk, 660037Ivan S. Yarkov
JSC Academician M. F. Reshetnev “Information Satellite Systems”
Email: yarkovis85@gmail.com
Design Engineer of the 2nd Category
Russian Federation, 52, Lenin St., Krasnoyarsk Region, Zheleznogorsk, 662971Evgeniya A. Yarkova
JSC Academician M. F. Reshetnev “Information Satellite Systems”
Email: Yarkova.sib@yandex.ru
Engineer for ASUP
Russian Federation, 52, Lenin St., Krasnoyarsk Region, Zheleznogorsk, 662971References
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