Satellite Orbit Modeling

Precise modeling of a satellite's perturbed motion (special perturbations approach)

Versione 4.2.1 (98,9 MB)
4,9K download
(19)
19 ago 2026

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This MATLAB package is a high-fidelity numerical orbit propagator for Earth satellites. It integrates the two-body equations of motion in the ICRF/EME2000 (J2000) inertial frame, with accelerations from Earth's spherical-harmonic gravity field, solid-Earth and ocean tides, third-body gravity (Sun, Moon, and planets), solar radiation pressure, atmospheric drag, and relativity. The demonstration driver test_Envisat.m propagates Envisat for 26.47 hours from a DORIS precise-orbit epoch and compares the result with the corresponding CNES DORIS POE.The implementation follows Montenbruck and Gill, Satellite Orbits: Models, Methods, and Applications (Springer, corrected 3rd printing, 2005); Vallado, Fundamentals of Astrodynamics and Applications (4th edition, 2013); and the IERS Conventions (2010) for tides, polar motion, and relativistic acceleration.

Cita come

Meysam Mahooti (2026). Satellite Orbit Modeling (https://it.mathworks.com/matlabcentral/fileexchange/54877-satellite-orbit-modeling), MATLAB Central File Exchange. Recuperato .

Categorie

Scopri di più su CubeSat and Satellites in Help Center e MATLAB Answers

Informazioni generali

Compatibilità della release di MATLAB

  • Compatibile con qualsiasi release

Compatibilità della piattaforma

  • Windows
  • macOS
  • Linux
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Versione Pubblicato Note della release
4.2.1

It was revised on 2026-08-20.
4.2.0

Line 129 of nrlmsise00.m was modified.
4.1.1

It was revised on 2025-06-23.
4.1.0

Ephemeris.m was modified.
4.0.0

Accel.m, AccelSolrad.m, and Conical.m were modified.
3.3.3

Accel.m and JPL_Eph_DE440.m were modified.
3.3.2

In nrlmsise00.m, flags.switches(1)=1; was fixed for output in meters and kilograms instead of centimeters and grams.
3.3.1

AccelHarmonic_AnelasticEarth.m and AccelHarmonic_ElasticEarth.m were modified.
3.3.0

Runge_Kutta_Fehlberg_7_8 was added. test_Envisat.m and Ephemeris.m were modified.
3.2.2

test_Envisat.m and nrlmsise00.m were modified.
3.2.1

The conical shadow model was added.
3.2.0

AccelHarmonic_AnelasticEarth.m and AccelHarmonic_ElasticEarth.m were modified, and a readme file was added.
3.1.1

nrlmsise00.m is modified.
3.1.0

The gast.m is modified.
3.0.0

Modifications are made to Mjday.m, invjday.m, test_Envisat.m, nrlmsise00.m, and Accel.m.
2.2.2.2

Modifications are made to SAT_Const.m, AccelHarmonic_AnelasticEarth.m, AccelHarmonic_ElasticEarth.m, and Accel.m.
2.2.2.1

The AccelHarmonic_AnelasticEarth.m, the AccelHarmonic_ElasticEarth.m, and the Accel.m are modified.
2.2.1.1

Mjday_TDB.m and nrlmsise00.m are modified.
2.1.1.1

The DE430 full matrix is added.
2.1.1.0

AccelHarmonic_ElasticEarth.m and AccelHarmonic_AnelasticEarth.m are modified.

2.1.0.0

AccelHarmonic_ElasticEarth.m, AccelHarmonic_AnelasticEarth.m, test_Envisat.m and InitialState.txt are modified.
2.0.0.1

Documentation is added.
2.0.0.0

Effect of solid Earth tides is computed for elastic and anelastic Earth based on IERS Conventions 2010 (AccelHarmonic_ElasticEarth.m, AccelHarmonic_AnelasticEarth.m).
SAT_Const.m is called once to decrease CPU time.
IERS.m, nrlmsise00.m, and test_Envisat.m are modified to decrease CPU time.
Ephemeris.m is modified to decrease CPU time.
DE405 (planetary and lunar ephemerides) is replaced by DE430.
Satellite's ground track is plotted.
1.1.0.0

Density_nrlmsise00.m is improved.
.
Integrator is changed.
.
.
The image is added.
Revised on 2016-11-29.
1.0.0.0