Научная электронная библиотека ULRICH'S Periodicals Directory

Сибирский государственный университет
науки и технологий имени академика М.Ф. Решетнева

Сибирский аэрокосмический журнал
ISSN 2712-8970 (Print) ISSN 2782-5760 (on-line)

Сведения об образовательной организации

UDK 536.2 Doi: 10.31772/2712-8970-2021-22-1-94-105
Parametric analysis of the anisogrid body of the spacecraft for cleaning the orbit of space debris
Belonovskaya I. D., Kolga V. V., Yarkov I. S., Yarkova E. A.
Orenburg State University; 13, Pobedy Av., Orenburg, 460018, Russian Federation. Reshetnev Siberian State University of Science and Technology; 31, Krasnoiarskii Rabochi Prospekt, Krasnoyarsk, 660037, Russian Federation. JSC Academician M. F. Reshetnev “Information Satellite Systems”; 52, Lenin St., Krasnoyarsk Region, Zheleznogorsk, 662971, Russian Federation.
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.
Keywords: spacecraft, parametric analysis, spacecraft strength, space debris collection, vibration frequency, stress-strain state, loss of stability, spacecraft design.
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Belonovskaya Izabella Davidovna – Dr. Sc., Professor, Professor of the Department of Mechanical Engineering Technology, Metalworking Machines and Complexes; Orenburg State University. E-mail: t251589@mail.ru.

Kolga Vadim Valentinovich – Dr. Sc., Professor, Professor of Department of Aircraft; Reshetnev Siberian State University of Science and Technology. E-mail: kolgavv@yandex.ru.

Yarkov Ivan Sergeevich – Design engineer of the 2nd category; JSC Academician M. F. Reshetnev “Information Satellite Systems”.
   Yarkova Evgeniya Aleksandrovna – Engineer for ASUP; JSC Academician M. F. Reshetnev “Information Satellite Systems”. E-mail: Yarkova.sib@yandex.ru.


  Parametric analysis of the anisogrid body of the spacecraft for cleaning the orbit of space debris