Abstract
The process of deployment and transfer to rotation with a given angular velocity of an electrodynamic space tether system in low Earth orbit is considered. The tether system is a linear grouping of three microsatellites connected by current-conducting insulated tethers. The process of forming a tether system is divided into two stages. At the first stage, there is no current in the tether and the relay law for the tension forces is used for the deployment of the system for a given length of the tether. At the second stage, with the help of current control, the system is transferred to a given final state of rotation with a constant angular velocity. To describe the motion of the centers of mass of microsatellites, the Lagrange equations are used. Under the condition of a slow change in tension forces, an analytical estimate was obtained for the characteristics of the angular motion of microsatellites relative to the direction of the tethers. The effectiveness of the considered approach to the formation of a rotating space tether system and the accuracy of analytical solutions are confirmed by numerical examples.
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Funding
The study was financially supported by the Russian Foundation for Basic Research and the SFES of China within the framework of the scientific project no. 20-51-53002.
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Translated by I. Katuev
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Zabolotnov, Y.M., Voevodin, P.S. & Hongshi, L. A TWO-STAGE METHOD FOR THE FORMATION OF A ROTATING ELECTRODYNAMIC SPACE TETHER SYSTEM. Mech. Solids 57, 462–475 (2022). https://doi.org/10.3103/S0025654422030232
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DOI: https://doi.org/10.3103/S0025654422030232