Electrodynamic Attitude Stabilization of a Spacecraft in an Elliptical Orbit
One of the fundamental problems of spacecraft dynamics related to ensuring its angular orientation in the basic coordinate system is considered. The problem of electrodynamic attitude control for a spacecraft in an elliptical near-Earth Keplerian orbit is studied. A mathematical model describing the...
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2024-11-01
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| Series: | Aerospace |
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| author | Maksim A. Klyushin Margarita V. Maksimenko Alexey A. Tikhonov |
| author_facet | Maksim A. Klyushin Margarita V. Maksimenko Alexey A. Tikhonov |
| author_sort | Maksim A. Klyushin |
| collection | DOAJ |
| description | One of the fundamental problems of spacecraft dynamics related to ensuring its angular orientation in the basic coordinate system is considered. The problem of electrodynamic attitude control for a spacecraft in an elliptical near-Earth Keplerian orbit is studied. A mathematical model describing the attitude dynamics of the spacecraft under the action of the Lorentz torque, the magnetic interaction torque, and the gravitational torque is constructed. The multipole model of the Earth’s magnetic field is used. The possibility of electrodynamic attitude control for the spacecraft’s angular stabilization in the orbital frame is analyzed based on the Euler–Poisson differential equations. The problem of electrodynamic compensation of disturbing torque due to the orbit eccentricity is solved. The control strategy for spacecraft electrodynamic attitude stabilization is presented. Electromagnetic parameters that allow stabilizing the spacecraft’s attitude position in the orbital frame are proposed. The disturbing gravity gradient torque is taken into account. The convergence of the control process is verified by computer modeling. Thus, the possibility and advisability of using the electrodynamic method for the spacecraft attitude control and its angular stabilization in the orbital coordinate system in an elliptical orbit is shown. |
| format | Article |
| id | doaj-art-ded8a5c23bc24db3bda559e2d3429737 |
| institution | OA Journals |
| issn | 2226-4310 |
| language | English |
| publishDate | 2024-11-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj-art-ded8a5c23bc24db3bda559e2d34297372025-08-20T01:53:48ZengMDPI AGAerospace2226-43102024-11-01111195610.3390/aerospace11110956Electrodynamic Attitude Stabilization of a Spacecraft in an Elliptical OrbitMaksim A. Klyushin0Margarita V. Maksimenko1Alexey A. Tikhonov2Department of Theoretical and Applied Mechaincs, Saint Petersburg State University, 7/9 Universitetskaya nab., St. Petersburg 199034, RussiaDepartment of Theoretical and Applied Mechaincs, Saint Petersburg State University, 7/9 Universitetskaya nab., St. Petersburg 199034, RussiaDepartment of Theoretical and Applied Mechaincs, Saint Petersburg State University, 7/9 Universitetskaya nab., St. Petersburg 199034, RussiaOne of the fundamental problems of spacecraft dynamics related to ensuring its angular orientation in the basic coordinate system is considered. The problem of electrodynamic attitude control for a spacecraft in an elliptical near-Earth Keplerian orbit is studied. A mathematical model describing the attitude dynamics of the spacecraft under the action of the Lorentz torque, the magnetic interaction torque, and the gravitational torque is constructed. The multipole model of the Earth’s magnetic field is used. The possibility of electrodynamic attitude control for the spacecraft’s angular stabilization in the orbital frame is analyzed based on the Euler–Poisson differential equations. The problem of electrodynamic compensation of disturbing torque due to the orbit eccentricity is solved. The control strategy for spacecraft electrodynamic attitude stabilization is presented. Electromagnetic parameters that allow stabilizing the spacecraft’s attitude position in the orbital frame are proposed. The disturbing gravity gradient torque is taken into account. The convergence of the control process is verified by computer modeling. Thus, the possibility and advisability of using the electrodynamic method for the spacecraft attitude control and its angular stabilization in the orbital coordinate system in an elliptical orbit is shown.https://www.mdpi.com/2226-4310/11/11/956spacecraftelliptical orbitelectrodynamic controlattitude stabilization |
| spellingShingle | Maksim A. Klyushin Margarita V. Maksimenko Alexey A. Tikhonov Electrodynamic Attitude Stabilization of a Spacecraft in an Elliptical Orbit Aerospace spacecraft elliptical orbit electrodynamic control attitude stabilization |
| title | Electrodynamic Attitude Stabilization of a Spacecraft in an Elliptical Orbit |
| title_full | Electrodynamic Attitude Stabilization of a Spacecraft in an Elliptical Orbit |
| title_fullStr | Electrodynamic Attitude Stabilization of a Spacecraft in an Elliptical Orbit |
| title_full_unstemmed | Electrodynamic Attitude Stabilization of a Spacecraft in an Elliptical Orbit |
| title_short | Electrodynamic Attitude Stabilization of a Spacecraft in an Elliptical Orbit |
| title_sort | electrodynamic attitude stabilization of a spacecraft in an elliptical orbit |
| topic | spacecraft elliptical orbit electrodynamic control attitude stabilization |
| url | https://www.mdpi.com/2226-4310/11/11/956 |
| work_keys_str_mv | AT maksimaklyushin electrodynamicattitudestabilizationofaspacecraftinanellipticalorbit AT margaritavmaksimenko electrodynamicattitudestabilizationofaspacecraftinanellipticalorbit AT alexeyatikhonov electrodynamicattitudestabilizationofaspacecraftinanellipticalorbit |