Non-coplanar rendezvous in near-circular orbit with the use a low thrust engine
Presented method allows one to calculate the of maneuvers performed on several turns using a low-thrust engine. These maneuvers ensure the flight of an active spacecraft within a given area of the target space object. The flight is carried out in the vicinity of a circular orbit. Simplified mathemat...
| Main Authors: | , |
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| Format: | Article |
| Language: | English |
| Published: |
Peoples’ Friendship University of Russia (RUDN University)
2024-03-01
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| Series: | RUDN Journal of Engineering Research |
| Subjects: | |
| Online Access: | https://journals.rudn.ru/engineering-researches/article/viewFile/38543/23308 |
| _version_ | 1797224996825726976 |
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| author | Andrey A. Baranov Adilson P. Olivio |
| author_facet | Andrey A. Baranov Adilson P. Olivio |
| author_sort | Andrey A. Baranov |
| collection | DOAJ |
| description | Presented method allows one to calculate the of maneuvers performed on several turns using a low-thrust engine. These maneuvers ensure the flight of an active spacecraft within a given area of the target space object. The flight is carried out in the vicinity of a circular orbit. Simplified mathematical models of motion are used to solve this problem. The influence of the non-centrality of the gravitational field and atmosphere is not taken into account in the calculations. The process of determining the parameters of the maneuvers is divided into several stages: in the first and third stages, the parameters of the impulse transfer and the transfer carried out by the low-thrust engine are calculated using analytical methods. In the second stage, the distribution of maneuvering between turns, ensuring a successful solution to the meeting problem, is determined by changing one variable. This method is characterized by its simplicity and high reliability in determining the parameters of maneuvers, which makes it applicable on board a spacecraft. As part of the study, an analysis of the dependence of the total characteristic velocity of solving the meeting problem on the amount of engine thrust was also carried out. The maneuver parameters can be refined using an iterative procedure to take into account the main disturbances. |
| first_indexed | 2024-04-24T14:02:00Z |
| format | Article |
| id | doaj.art-2c5047864d1d4a9588d3da12809483c2 |
| institution | Directory Open Access Journal |
| issn | 2312-8143 2312-8151 |
| language | English |
| last_indexed | 2024-04-24T14:02:00Z |
| publishDate | 2024-03-01 |
| publisher | Peoples’ Friendship University of Russia (RUDN University) |
| record_format | Article |
| series | RUDN Journal of Engineering Research |
| spelling | doaj.art-2c5047864d1d4a9588d3da12809483c22024-04-03T12:34:27ZengPeoples’ Friendship University of Russia (RUDN University)RUDN Journal of Engineering Research2312-81432312-81512024-03-0125172010.22363/2312-8143-2024-25-1-7-2021109Non-coplanar rendezvous in near-circular orbit with the use a low thrust engineAndrey A. Baranov0https://orcid.org/0000-0003-1823-9354Adilson P. Olivio1https://orcid.org/0000-0001-5632-3747Keldysh Institute of Applied Mathematics, Russian Academy of SciencesRUDN UniversityPresented method allows one to calculate the of maneuvers performed on several turns using a low-thrust engine. These maneuvers ensure the flight of an active spacecraft within a given area of the target space object. The flight is carried out in the vicinity of a circular orbit. Simplified mathematical models of motion are used to solve this problem. The influence of the non-centrality of the gravitational field and atmosphere is not taken into account in the calculations. The process of determining the parameters of the maneuvers is divided into several stages: in the first and third stages, the parameters of the impulse transfer and the transfer carried out by the low-thrust engine are calculated using analytical methods. In the second stage, the distribution of maneuvering between turns, ensuring a successful solution to the meeting problem, is determined by changing one variable. This method is characterized by its simplicity and high reliability in determining the parameters of maneuvers, which makes it applicable on board a spacecraft. As part of the study, an analysis of the dependence of the total characteristic velocity of solving the meeting problem on the amount of engine thrust was also carried out. The maneuver parameters can be refined using an iterative procedure to take into account the main disturbances.https://journals.rudn.ru/engineering-researches/article/viewFile/38543/23308spacecraftnear-circular orbitvelocity impulsecalculation of maneuver parametersspace objectlow thrust engine |
| spellingShingle | Andrey A. Baranov Adilson P. Olivio Non-coplanar rendezvous in near-circular orbit with the use a low thrust engine RUDN Journal of Engineering Research spacecraft near-circular orbit velocity impulse calculation of maneuver parameters space object low thrust engine |
| title | Non-coplanar rendezvous in near-circular orbit with the use a low thrust engine |
| title_full | Non-coplanar rendezvous in near-circular orbit with the use a low thrust engine |
| title_fullStr | Non-coplanar rendezvous in near-circular orbit with the use a low thrust engine |
| title_full_unstemmed | Non-coplanar rendezvous in near-circular orbit with the use a low thrust engine |
| title_short | Non-coplanar rendezvous in near-circular orbit with the use a low thrust engine |
| title_sort | non coplanar rendezvous in near circular orbit with the use a low thrust engine |
| topic | spacecraft near-circular orbit velocity impulse calculation of maneuver parameters space object low thrust engine |
| url | https://journals.rudn.ru/engineering-researches/article/viewFile/38543/23308 |
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