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Cosmic Research

, Volume 55, Issue 4, pp 270–274 | Cite as

Controlling the motion of a spacecraft when approaching a large object of space debris

  • A. A. Baranov
  • A. A. Budyanskiy
  • Yu. N. Razumnyi
Article
  • 30 Downloads

Abstract

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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Copyright information

© Pleiades Publishing, Ltd. 2017

Authors and Affiliations

  • A. A. Baranov
    • 1
    • 2
    • 3
  • A. A. Budyanskiy
    • 1
  • Yu. N. Razumnyi
    • 3
  1. 1.Keldysh Institute of Applied MathematicsRussian Academy of SciencesMoscowRussia
  2. 2.Bauman Moscow State Technical UniversityMoscowRussia
  3. 3.RUDN UniversityMoscowRussia

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