Modeling and comparative analysis of schemes for returning a payload using a space tethered system

Z. Dong; Y. M. Zabolotnov; A. J. Li; C. Q. Wang

doi:10.1088/1742-6596/1368/4/042010

Modeling and comparative analysis of schemes for returning a payload using a space tethered system

Z. Dong, Y. M. Zabolotnov, A. J. Li, C. Q. Wang

School of Automation

Samara National Research University

Research output: Contribution to journal › Conference article › peer-review

1 Scopus citations

Abstract

The multiple schemes for returning a payload from LEO using a space tethered system are designed and analyzed in this paper. The space tethered system consists of a main spacecraft, a tether, a returning capsule with the payload (or space debris) and an atmospheric probe. The simulation for the motion of the tethered system is based on a mathematical model with distributed parameters, in which the tether is considered as a sequence of point masses with one-sided elastic mechanical coupling. The aerodynamic forces acting on all parts of the tethered system including on the tether are considered in this work. The atmospheric probe is used as an additional braking device for the proposed schemes for returning the payload.

Original language	English
Article number	042010
Journal	Journal of Physics: Conference Series
Volume	1368
Issue number	4
DOIs	https://doi.org/10.1088/1742-6596/1368/4/042010
State	Published - 27 Nov 2019
Event	5th International Conference on Information Technology and Nanotechnology, ITNT 2019 - Samara, Russian Federation Duration: 21 May 2019 → 24 May 2019

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10.1088/1742-6596/1368/4/042010

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abstract = "The multiple schemes for returning a payload from LEO using a space tethered system are designed and analyzed in this paper. The space tethered system consists of a main spacecraft, a tether, a returning capsule with the payload (or space debris) and an atmospheric probe. The simulation for the motion of the tethered system is based on a mathematical model with distributed parameters, in which the tether is considered as a sequence of point masses with one-sided elastic mechanical coupling. The aerodynamic forces acting on all parts of the tethered system including on the tether are considered in this work. The atmospheric probe is used as an additional braking device for the proposed schemes for returning the payload.",

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AB - The multiple schemes for returning a payload from LEO using a space tethered system are designed and analyzed in this paper. The space tethered system consists of a main spacecraft, a tether, a returning capsule with the payload (or space debris) and an atmospheric probe. The simulation for the motion of the tethered system is based on a mathematical model with distributed parameters, in which the tether is considered as a sequence of point masses with one-sided elastic mechanical coupling. The aerodynamic forces acting on all parts of the tethered system including on the tether are considered in this work. The atmospheric probe is used as an additional braking device for the proposed schemes for returning the payload.

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Modeling and comparative analysis of schemes for returning a payload using a space tethered system

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