Controlling the motion of a spacecraft when approaching a large object of space debris |
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Authors: | Email author" target="_blank">A?A?BaranovEmail author A?A?Budyanskiy Yu?N?Razumnyi |
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Institution: | 1.Keldysh Institute of Applied Mathematics,Russian Academy of Sciences,Moscow,Russia;2.Bauman Moscow State Technical University,Moscow,Russia;3.RUDN University,Moscow,Russia |
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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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