Keplerian Orbit
This contribution contains an algorithm to calculate the orbit of a satellite according to the third law of Kepler and Newton's law of gravitation.
The program loads input data from a file of type two-line elements (TLE).
An input TLE file: https://www.dropbox.com/s/lezxmsxnn6vai5n/TLE_skCUBE.txt?dl=0
TLE file type, information about satellite skCUBE is described in the following article:
Szabó, P., Gombíková, K., Ferencová, M. and Košuda, M.:"Keplerian Orbit and Satellite skCUBE",
2019 New Trends in Aviation Development (NTAD), pp. 174-179, IEEE,
https://ieeexplore.ieee.org/document/8875530
This program is a part of a diploma thesis. Author and title of thesis:
Katarína Gombíková: MATLAB for flight engineers (2020).
Citar como
Peter Szabó and Katarína Gombíková (2019). Keplerian Orbit (https://www.mathworks.com/matlabcentral/fileexchange/72098), MATLAB Central File Exchange. Retrieved July 11, 2019.
Compatibilidad con la versión de MATLAB
Compatibilidad con las plataformas
Windows macOS LinuxCategorías
- Sciences > Physics > Gravitation, Cosmology & Astrophysics >
- MATLAB > External Language Interfaces > Other languages > DropBox >
- Engineering > Aerospace Engineering > Satellite and Orbital Mechanics >
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Versión | Publicado | Notas de la versión | |
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1.0.7 | minor output fixes |
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1.0.6 | minor text fixes |
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1.0.5 | Adding a reference to the program. |
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1.0.4 | 1.0.4
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1.0.3 | 1.0.3
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1.0.2 | 1.0.2
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1.0.1 | 1.0.1
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1.0.0 |