Satellite Orbit Computation
A modified version of the SGP4 code used for standard satellite orbit computation using two-line elements (TLE). The modified code outputs satellite positions and velocity in ECF coordinates and universal time from EPOCH. Utilities are provided to calculate point-to-point angle, range rates, TCS positions, constant altitude intercepts and velocities. Outputs are collected in a structure and retained in a *.mat file for subsequent display and Beacon satellite data analysis applications. Documentation and examples are provided. Code uses GPS_CoordinateXform and IGRF utilities available from MATLAB Central.
Citation pour cette source
Charles Rino (2024). Satellite Orbit Computation (https://www.mathworks.com/matlabcentral/fileexchange/28888-satellite-orbit-computation), MATLAB Central File Exchange. Récupéré le .
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- Industries > Aerospace and Defense > CubeSat and Satellites >
- Aerospace > Aerospace Blockset > Reference Applications >
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SGP4/
SatGeom_Example/
utilities/
Version | Publié le | Notes de version | |
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1.3.0.0 | Corrected error in satGEOM utility. SGP4 is unaffected. |
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1.2.0.0 | Error corrected in function satGEOM. Only affects results that use magnetic field geometry. |
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1.0.0.0 |