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
Highlights
The low-orbit satellite groups Starlink and Oneweb, launched over recent years, whose quantity is expected to exceed 12,000 units, will make the already busy space environment in low orbits much more difficult
The aim of this study is to develop a combined method for removing the large-sized space objects (SOs) from low-Earth orbits using electric rocket propulsion systems (ERPS) as an active means of de-orbiting
We have designed a scheme for the de-orbiting of large-sized SOs from the low near-Earth orbits using a combined method taking into consideration the implementation of the features of ERPS operation
Summary
The low-orbit satellite groups Starlink and Oneweb, launched over recent years, whose quantity is expected to exceed 12,000 units, will make the already busy space environment in low orbits much more difficult. A relatively recent emergency involved the Starlink-44 and Aeolus satellites, which forced the latter to maneuver on February 9, 2020, to avoid a collision. The large-sized non-functioning SOs are even more dangerous [2, 3]: spacecraft and the upper stages of launch vehicles. A collision with them is highly likely to lead to the shutdown of the existing satellite. The many debris created by the collision can lead to the beginning of an avalanche-like increase in the number of near-Earth SOs, called Kessler Syndrome [1, 4, 5]
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More From: Eastern-European Journal of Enterprise Technologies
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