Coplanar multi-turn rendezvous in near-circular orbit using a low-thrust engine
The authors describe an algorithm that allows calculating the parameters of maneuvers performed on several turns by the low-thrust engine, which ensure the flight of the active spacecraft to the specified vicinity of the target space object. The movement takes place in the vicinity of a circular orb...
| Main Authors: | , |
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| Format: | Article |
| Language: | English |
| Published: |
Peoples’ Friendship University of Russia (RUDN University)
2022-12-01
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| Series: | RUDN Journal of Engineering Research |
| Subjects: | |
| Online Access: | https://journals.rudn.ru/engineering-researches/article/viewFile/33690/21730 |
| _version_ | 1827977067151491072 |
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| author | Andrey A. Baranov Adilson Pedro Olivio |
| author_facet | Andrey A. Baranov Adilson Pedro Olivio |
| author_sort | Andrey A. Baranov |
| collection | DOAJ |
| description | The authors describe an algorithm that allows calculating the parameters of maneuvers performed on several turns by the low-thrust engine, which ensure the flight of the active spacecraft to the specified vicinity of the target space object. The movement takes place in the vicinity of a circular orbit. Linearized equations of motion are used in solving the problem. The influence of the non-centrality of the gravitational field and the atmosphere is not taken into account. The determination of maneuver parameters takes place in three stages. At the first and third stages, the parameters of the pulse transition and the transition performed by the low-thrust engine, are determined analytically. At the second stage, the distribution of maneuvering between turns, which provides a solution to the meeting problem, is carried out by iterating over one variable. This method of solving the problem provides simplicity and high reliability of determining the parameters of maneuvers, which allows it to be used on board the spacecraft. The paper investigates the dependence of the total characteristic speed of solving the meeting problem on the number of turns of the flight and the magnitude of the engine thrust. |
| first_indexed | 2024-04-09T20:58:13Z |
| format | Article |
| id | doaj.art-0e240c2322bf4799be2287ba76ea01c5 |
| institution | Directory Open Access Journal |
| issn | 2312-8143 2312-8151 |
| language | English |
| last_indexed | 2024-04-09T20:58:13Z |
| publishDate | 2022-12-01 |
| publisher | Peoples’ Friendship University of Russia (RUDN University) |
| record_format | Article |
| series | RUDN Journal of Engineering Research |
| spelling | doaj.art-0e240c2322bf4799be2287ba76ea01c52023-03-29T12:34:19ZengPeoples’ Friendship University of Russia (RUDN University)RUDN Journal of Engineering Research2312-81432312-81512022-12-0123428329210.22363/2312-8143-2022-23-4-283-29221068Coplanar multi-turn rendezvous in near-circular orbit using a low-thrust engineAndrey A. Baranov0https://orcid.org/0000-0003-1823-9354Adilson Pedro Olivio1https://orcid.org/0000-0001-5632-3747Keldysh Institute of Applied Mathematics, Russian Academy of SciencesPeoples’ Friendship University of Russia (RUDN University)The authors describe an algorithm that allows calculating the parameters of maneuvers performed on several turns by the low-thrust engine, which ensure the flight of the active spacecraft to the specified vicinity of the target space object. The movement takes place in the vicinity of a circular orbit. Linearized equations of motion are used in solving the problem. The influence of the non-centrality of the gravitational field and the atmosphere is not taken into account. The determination of maneuver parameters takes place in three stages. At the first and third stages, the parameters of the pulse transition and the transition performed by the low-thrust engine, are determined analytically. At the second stage, the distribution of maneuvering between turns, which provides a solution to the meeting problem, is carried out by iterating over one variable. This method of solving the problem provides simplicity and high reliability of determining the parameters of maneuvers, which allows it to be used on board the spacecraft. The paper investigates the dependence of the total characteristic speed of solving the meeting problem on the number of turns of the flight and the magnitude of the engine thrust.https://journals.rudn.ru/engineering-researches/article/viewFile/33690/21730spacecraftcalculation of maneuver parametersspace objectlow-thrust enginecircular orbitvelocity impulse |
| spellingShingle | Andrey A. Baranov Adilson Pedro Olivio Coplanar multi-turn rendezvous in near-circular orbit using a low-thrust engine RUDN Journal of Engineering Research spacecraft calculation of maneuver parameters space object low-thrust engine circular orbit velocity impulse |
| title | Coplanar multi-turn rendezvous in near-circular orbit using a low-thrust engine |
| title_full | Coplanar multi-turn rendezvous in near-circular orbit using a low-thrust engine |
| title_fullStr | Coplanar multi-turn rendezvous in near-circular orbit using a low-thrust engine |
| title_full_unstemmed | Coplanar multi-turn rendezvous in near-circular orbit using a low-thrust engine |
| title_short | Coplanar multi-turn rendezvous in near-circular orbit using a low-thrust engine |
| title_sort | coplanar multi turn rendezvous in near circular orbit using a low thrust engine |
| topic | spacecraft calculation of maneuver parameters space object low-thrust engine circular orbit velocity impulse |
| url | https://journals.rudn.ru/engineering-researches/article/viewFile/33690/21730 |
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