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

Golubek, Aleksandr; Dron, Mykola; Dubovik, L.G.; Dreus, Andrii; Kulyk, Oleksii; Khorolskiy, Petro

doi:10.15587/1729-4061.2020.210378

Cited by 14 publications

(11 citation statements)

References 30 publications

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“…The use of reusable engines and the choice of a circuit for turning on the jet engine installation (JEI) will increase the efficiency of the combined method for de-orbiting largesized space objects. Unlike the existing active and passive techniques, using the combined de-orbiting will make it possible to ensure the removal of space debris objects from the earth's orbit within a specified period and with minimal fuel consumption [14,[30][31][32].…”

Section: Discussion Of Results Of the Substantiation Of The Choice Of...mentioning

confidence: 99%

“…Methods for removing space objects from near-Earth orbits are divided into active and passive [13]. More scientific research is emerging that focuses on the development of combined methods for the removal of space objects from near-Earth orbits as a combination of active and passive techniques [14]. Given the prospects of the combined method as an alternative competitive system to other systems for cleaning the Earth's orbit, it is necessary to scientifically justify the design of the combined removal of space objects into the dense layers of the Earth's atmosphere.…”

Section: Literature Review and Problem Statementmentioning

confidence: 99%

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Determining the performance indicators of employing combined methods for removing space objects from near-earth orbits

Dron’

Hilorme

Golubek

et al. 2022

EEJET

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A methodology for assessing the relative effectiveness of alternative options for building space object diversion systems has been improved. An algorithm for assessing the effectiveness of the system of removal of space objects from near-Earth orbit based on the method of integral assessment is given. It makes it possible to simplify the process of optimal choice of the method to divert space objects and determine efficiency in the early phases of the life cycle of rocket and space technology objects. The use of the appropriate toolset makes it possible to build a system for assessing the effectiveness of projects for the removal of space objects from low Earth orbits using various diversion methods (active, passive, combined). The analysis of defining world indicators of evaluation of objects of rocket and space technology based on regulations by international space agencies has been carried out. An indicator of the total integrated relative efficiency of projects of space object diversion systems from low Earth orbits has been proposed, which makes it possible to build the removal of passive, active, and combined methods for leveling the risks of space activities. It is argued that the selected combined system using an autophagic launch vehicle could reduce environmental losses and, as a result, reduce compensation payments to owners of space objects. The possibilities of building combined systems with reusable engines have been considered in order to reduce such indicators as the period of diversion and reduction of operating costs due to fuel economy.

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Section: Discussion Of Results Of the Substantiation Of The Choice Of...mentioning

confidence: 99%

Section: Literature Review and Problem Statementmentioning

confidence: 99%

Determining the performance indicators of employing combined methods for removing space objects from near-earth orbits

Dron’

Hilorme

Golubek

et al. 2022

EEJET

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“…The reliability of simulation is ensured through the use of verified fundamental equations of dynamics and thermodynamics of an aircraft in the Earth's atmosphere (Loh, 1960). The effectiveness of this approach is also confirmed in works (Golubek et al, 2020). In accordance with this methodology, the trajectory of the launch vehicle in the atmosphere is described by the system of equations as follows:…”

Section: Motion Simulation At the Atmospheric Phasementioning

confidence: 97%

A simulation of the thermal environment of a plastic body of a new type of launch vehicle at the atmospheric phase of the trajectory

Dreus

Yemets

Dron

et al. 2021

AEAT

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Purpose Leading developers and providers in the modern space launch market note a splash in the development of ultralight launch vehicle (LV), driven by the growing demand for small satellites for large constellations in low Earth orbits. One of the promising ways to solve the problem of the quick launch of such satellites is to use a new type of ultralight launch vehicle with a plastic body. The project of such a launch vehicle was proposed by Oles Honchar Dnipro National University (Ukraine). Along with that, there is a need for appropriate research studies on the thermal resistance of the plastic shell, as the physical, mechanical and thermophysical characteristics of polymers significantly differ from traditional aerospace materials. The purpose of this study is to validate the design and ballistic parameters of such a launch vehicle in terms of providing an acceptable thermal environment at the atmospheric phase of the trajectory. Design/methodology/approach The workability of a new type of propulsion system is being investigated experimentally in bench conditions. To study the process of aerodynamic heating of a plastic shell, numerical modeling based on the integration of the flight dynamics and heat transfer equations is used. Findings Brief information about the design of a new type of ultra-light autophage launch vehicle with a plastic body is presented. A mathematical model for the movement of the launch vehicle at the atmospheric phase of the trajectory, and for the heating of the polyethylene body of the launch vehicle, taking into account the dynamic change in the atmospheric parameters is proposed. The influence of the motion trajectory on the thermal environment of the rocket body is investigated, rational motion trajectories and corresponding permissible g-loads are determined. Originality/value The fundamental possibility of using plastic (polyethylene) as a structural material and fuel for bodies of a new type of ultralight launch vehicles has been substantiated. It is shown that to ensure acceptable thermal conditions of a plastic body, it is necessary to use thermal insulation. It is proposed to use a polymeric Teflon coating as such thermal insulation. The results are important for the development of technologies for launching small satellites into orbit, as the use of plastic as the main structural material of the rocket body will significantly reduce the launch cost.

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“…They suggest putting efforts to shorten the lifetime of debris or debris removal operation should not create more debris (Krisko et al, 2001;Butterworth-Heinemann et al, 2010b;Martinez and Kendall, 2019; United Nations Office for Outher Space Affairs, 2019). There are advanced mathematical methods to use the remnant propellant of the Jet Propulsion System (JPS) (Golubek et al, 2019), or an even more energy-efficient Electric Rocket Propulsion System (ERPS) (Golubek et al, 2020), for optimal de-orbiting operation. However, the satellites already placed in orbits were not designed to satisfy the abovementioned properties.…”

Section: The Problemmentioning

confidence: 99%

ET-Class: An Energy Transfer-Based Classification of Space Debris Removal Methods and Missions

Yalçin¹,

Martinez²,

Delisle³

et al. 2022

Front. Space Technol.

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Space debris is positioned as a fatal problem for current and future space missions. Many effective space debris removal methods have been proposed in the past decade, and several techniques have been either tested on the ground or in parabolic flight experiments. Nevertheless, no uncooperative debris has been removed from any orbit until this moment. Therefore, to expand this research field and progressing the development of space debris removal technologies, this paper reviews and compares the existing technologies with past, present, and future methods and missions. Moreover, since one of the critical problems when designing space debris removal solutions is how to transfer the energy between the chaser/de-orbiting kit and target during the first interaction, this paper proposes a novel classification approach, named ET-Class (Energy Transfer Class). This classification approach provides an energy-based perspective to the space debris phenomenon by classifying how existing methods dissipate or store energy during the first contact.

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

Cited by 14 publications

References 30 publications

Determining the performance indicators of employing combined methods for removing space objects from near-earth orbits

Determining the performance indicators of employing combined methods for removing space objects from near-earth orbits

A simulation of the thermal environment of a plastic body of a new type of launch vehicle at the atmospheric phase of the trajectory

ET-Class: An Energy Transfer-Based Classification of Space Debris Removal Methods and Missions

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