The problem of calculating the parameters of maneuvering a spacecraft as it approaches a large object of space debris (LOSD) in close near-circular noncoplanar orbits has been considered. In [1–4], the results of analyzing the problem of the flyby of the separated LOSD groups have been presented. It has been assumed that a collector spacecraft approaches the LOSD and captures it or it is inserted into the nozzle of a small spacecraft that has a proper propulsion system (PS). However, in these papers, the flight from one object to another was only analyzed and the problem of approaching to LOSD with a given accuracy was not considered. This paper is a supplement to the cycle of papers [1–4]. It is assumed that, the final stage of approaching the LOSD is implemented by maneuvering in many orbits (up to several dozens) with low-thrust engines, but the PS operating time is fairly small compared with the orbit period in order to make it possible to use impulse approximation in the calculations.
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Original Russian Text © A.A. Baranov, A.A. Budyanskiy, Yu.N. Razumnyi, 2017, published in Kosmicheskie Issledovaniya, 2017, Vol. 55, No. 4, pp. 285–289.
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Baranov, A.A., Budyanskiy, A.A. & Razumnyi, Y.N. Controlling the motion of a spacecraft when approaching a large object of space debris. Cosmic Res 55, 270–274 (2017). https://doi.org/10.1134/S0010952517040013