Abstract
An analysis of the motion of a deployed space system that consists of two end bodies connected by a tether has been considered. One of the bodies has a relatively large ballistic coefficient that ensures aerodynamic braking or the stabilization of the motion of the entire system in relatively low near-Earth orbits. The deployment of this system mainly occurs due to the action of aerodynamic forces. Several ways of deploying the system have been analyzed, including (1) the uncontrolled release of the tether with hardly any braking; (2) deployment with constant braking force; (3) the dynamic control law without feedback, when the resistance force varies according to a set program; (4) a kinematic control law with feedback when programs are set for varying the velocity and length of the tether release. To analyze the dynamics of the system, a mathematical model of motion has been constructed in which the motion of the end bodies relative to their centers of mass is taken into account.
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Original Russian Text © D.V. Elenev, Yu.M. Zabolotnov, 2017, published in Kosmicheskie Issledovaniya, 2017, Vol. 55, No. 5, pp. 379–387.
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Elenev, D.V., Zabolotnov, Y.M. Analysis of the dynamics of the deployed aerodynamic space tether system. Cosmic Res 55, 371–379 (2017). https://doi.org/10.1134/S0010952517050057
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DOI: https://doi.org/10.1134/S0010952517050057