Development of the combined method to de-orbit space objects using an electric rocket propulsion system

Authors

DOI:

https://doi.org/10.15587/1729-4061.2020.210378

Keywords:

large-sized space debris, combined de-orbiting, electric rocket propulsion system, low orbits

Abstract

A method has been developed for the combined de-orbiting of large-size objects of space debris from low-Earth orbits using an electro-rocket propulsion system as an active de-orbiting means.

A principal de-orbiting technique has been devised, which takes into consideration the patterns of using an electric rocket propulsion system in comparison with the sustainer rocket propulsion system.

A procedure for determining the parameters of the de-orbiting scheme has been worked out, such as the minimum total speed and the time of the start of the de-orbiting process, which ensures its achievement. The proposed procedure takes into consideration the impact exerted on the process of the de-orbiting by the ballistic factor of the object, the height of the initial orbit, and the phase of solar activity at the time of the de-orbiting onset. The actual time constraints on battery discharge have been accounted for, as well as on battery charge duration, and active operation of the control system.

The process of de-orbiting a large-size object of space debris has been simulated by using the combined method involving an electro-rocket propulsion system. The impact of the initial orbital altitude, ballistic coefficient, and the phase of solar activity on the energy costs of the de-orbiting process have been investigated. The dependences have been determined of the optimal values of a solar activity phase, in terms of energy costs, at the moment of the de-orbiting onset, and the total velocity, required to ensure the de-orbiting, on the altitude of the initial orbit and ballistic factor. These dependences are of practical interest in the tasks of designing the means of the combined de-orbiting involving an electric rocket propulsion system. The dependences of particular derivatives from the increment of a velocity pulse to the gain in the ballistic factor on the altitude of the initial orbit have been established. The use of these derivatives is also of practical interest to assess the effect of unfolding an aerodynamic sailing unit

Author Biographies

Aleksandr Golubek, Yuzhnoye Design Office Kryvorizhska str., 3, Dnipro, Ukraine, 49008

PhD, Associate Professor, Lead Software Engineer

Department of Design and Theoretical Works

Mykola Dron’, Oles Нonchar Dnipro National University Gagarina ave., 72, Dnipro, Ukraine, 49010

Doctor of Technical Sciences, Professor

Department of Design and Construction

Ludmila Dubovik, Oles Нonchar Dnipro National University Gagarina ave., 72, Dnipro, Ukraine, 49010

Senior Researcher

Institute of Energy

Andrii Dreus, Oles Нonchar Dnipro National University Gagarina ave., 72, Dnipro, Ukraine, 49010

Doctor of Technical Sciences, Associate Professor

Department of Fluid Mechanics and Energy and Mass Transfer

Oleksii Kulyk, The National Aerospace Educational Center of Youth Named After А. М. Makarov Gagarina ave., 26, Dnipro, Ukraine, 409005

PhD, Associate Professor, General Director

Petro Khorolskiy, Yuzhnoye Design Office Kryvorizhska str., 3, Dnipro, Ukraine, 49008

PhD, Head of Sector

Department of Design and Theoretical Works

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Published

2020-08-31

How to Cite

Golubek, A., Dron’, M., Dubovik, L., Dreus, A., Kulyk, O., & Khorolskiy, P. (2020). Development of the combined method to de-orbit space objects using an electric rocket propulsion system. Eastern-European Journal of Enterprise Technologies, 4(5 (106), 78–87. https://doi.org/10.15587/1729-4061.2020.210378

Issue

Vol. 4 No. 5 (106) (2020): Applied physics

Section

Applied physics

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Copyright (c) 2020 Aleksandr Golubek, Mykola Dron’, Ludmila Dubovik, Andrii Dreus, Oleksii Kulyk, Petro Khorolskiy

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