Cite this article as:
Ryazanov V. V., Ledkov A. S. Descent of Nanosatellite from Low Earth Orbit by Ion Beam. Izv. Saratov Univ. (N. S.), Ser. Math. Mech. Inform., 2019, vol. 19, iss. 1, pp. 82-93. DOI: https://doi.org/10.18500/1816-9791-2019-19-1-82-93
Descent of Nanosatellite from Low Earth Orbit by Ion Beam
The work is devoted to the problem of contactless CubSat3U nanosatellites removal from low Earth orbit bymean sof anion beam, which is created by the engine of an active spacecraft. The advant age of this methodis that there is no needfor additional mean sof dockingand gripping. A mathematical model of the nanosatellite plane motion under the action of the ion beam and gravitational forces is developed. Two approaches are used to simulate the ion beam impacton nano satellite.The first one involves the use of known dimensionless aerodynamic coefficients. The second approach is based on the division of the body into triangles and the calculation of the effect of the beam on each of them. Wherein the hypothesis of a complete diffuse reflection of particles from the surface of the body is used. The descent of the nanosatellite from a low Earth orbit to the surface has been simulated. It is shown that both approaches give close results, in particular, the difference in the descent time from analtitude of 500 km does notexceed 4%. The closeness of the result sallows to use aerodynamic characteristics at the stage of preliminary design of the non-functioning satellite removal missions. The obtained results can be used for the ion beam control development and for modeling the motion of the system of contactless space debris removal.
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