Keplerian Orbit

バージョン 1.0.7 (145 KB) 作成者: Peter Szabó
A program for computation an orbit of a satellite by third Kepler law.
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更新 2019/11/2

ライセンスの表示

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).

引用

Peter Szabó and Katarína Gombíková (2019). Keplerian Orbit (https://www.mathworks.com/matlabcentral/fileexchange/72098), MATLAB Central File Exchange. Retrieved July 11, 2019.

MATLAB リリースの互換性
作成: R2019b
R2018b 以降のリリースと互換性あり
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バージョン 公開済み リリース ノート
1.0.7

minor output fixes
1.0.6

minor text fixes
1.0.5

Adding a reference to the program.
1.0.4

1.0.4
- O = Omega (program note, MATLAB variables)
1.0.3

1.0.3
- software description update
1.0.2

1.0.2
- description update
1.0.1

1.0.1
- Adding a link to an input file
- Diploma thesis information
1.0.0