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

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. © 2017, Pleiades Publishing, Ltd.

Авторы
Baranov A.A. 1, 2, 3 , Budyanskiy A.A.1 , Razumnyi Y.N. 3
Редакторы
-
Журнал
Издательство
Maik Nauka Publishing / Springer SBM
Номер выпуска
4
Язык
Английский
Страницы
270-274
Статус
Опубликовано
Подразделение
-
Номер
-
Том
55
Год
2017
Организации
  • 1 Keldysh Institute of Applied Mathematics, Russian Academy of Sciences, Moscow, 125047, Russian Federation
  • 2 Bauman Moscow State Technical University, Moscow, 105005, Russian Federation
  • 3 RUDN University, Moscow, 117198, Russian Federation
Ключевые слова
-
Дата создания
19.10.2018
Дата изменения
19.10.2018
Постоянная ссылка
https://repository.rudn.ru/ru/records/article/record/5452/