Methodology of designing a small spacecraft for technological purposes
https://doi.org/10.25206/2588-0373-2024-8-4-73-79
EDN: TTAAOV
Abstract
The paper presents a methodology for designing a small spacecraft to perform the tasks of technological processes in near-Earth space. When designing such a small spacecraft, it is assumed that it will be equipped with a microgravity platform to meet the requirements for micro-accelerations. The methodology is based on the principles of individuality, attainability and controllability. They guarantee the maximum possible consideration of the features of the gravity-sensitive process being implemented, including compliance with the requirements for limiting the micro-acceleration module in the working area of technological equipment and effective control of this implementation. The developed technique can be used in the design of a small spacecraft for technological purposes.
Keywords
design methodology,
micro-acceleration,
gravity-sensitive processes,
microgravity platform,
small spacecraft,
technological purpose,
vibration protection device
Supporting agencies: The work is carried out within the framework of the State task of the Ministry of Science and Higher Education of the Russian Federation (Project FSSS- 2023-0007).
About the Authors
A. V. Sedelnikov
Samara National Research University
Russian Federation
Russian Federation
SEDELNIKOV Andrey Valeryevich, Doctor of Technical Sciences, Professor, Professor of Space Engineering Department
Samara
AuthorID (SCOPUS): 23013232300
ResearcherID: G-4444-2017
A. S. Taneeva
Samara National Research University
Russian Federation
Russian Federation
TANEEVA Anastasiya Sergeevna, Graduate Student of Space Engineering Department, Engineer of NII-219 (Research Institute of Space Engineering), Engineer and Assistant of Space Engineering Department
Samara
AuthorID (SCOPUS): 57205365815
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For citations:
Sedelnikov A.V., Taneeva A.S. Methodology of designing a small spacecraft for technological purposes. Omsk Scientific Bulletin. Series Aviation-Rocket and Power Engineering. 2024;8(4):73-79. (In Russ.) https://doi.org/10.25206/2588-0373-2024-8-4-73-79. EDN: TTAAOV
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