High Precision Orbit Propagator

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

Version 4.3.0 (99.6 MB)
8.2K Downloads
(32)
20 Aug 2026

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This package integrates the translational equations of motion of an Earth satellite in the International Celestial Reference Frame (ICRF / EME2000). The right-hand side in Accel.m assembles Newtonian gravity, third-body perturbations, non-conservative surface forces, and post-Newtonian corrections. Time, Earth orientation, and the celestial-to-terrestrial transformation follow IAU 2006/2000A (CIO-based) as implemented in the included SOFA MATLAB ports (iau*.m), aligned with SOFA release 2023-10-11. SOFA sofam.h macros and the remaining astronomical constants are in SAT_Const.m.The driver test_HPOP.m propagates Envisat from a DORIS precise-orbit epoch on 24 April 2002, 21:55:28 UTC, for 1 588 steps of 60 s (26.47 hours). The default flags leave albedo, ocean tides, and relativity off, which gives closer agreement with the bundled DORIS precise orbit. The integrated ITRS trajectory is compared with the published DORIS/Envisat states in True_EnvisatStates.m.

Cite As

Meysam Mahooti (2026). High Precision Orbit Propagator (https://in.mathworks.com/matlabcentral/fileexchange/55167-high-precision-orbit-propagator), MATLAB Central File Exchange. Retrieved .

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General Information

MATLAB Release Compatibility

  • Compatible with any release

Platform Compatibility

  • Windows
  • macOS
  • Linux
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Version Published Release Notes
4.3.0

It was revised on 2026-08-20.
4.2.2

It was revised on 2025-06-24.
4.2.1

Accel.m, AccelSolrad.m, and Conical.m were modified.
4.2.0

test_HPOP.m, Accel.m, JPL_Eph_DE440.m, and nrlmsise00.m were modified.
4.1.1

AccelHarmonic_AnelasticEarth.m and AccelHarmonic_ElasticEarth.m were modified.
4.1.0

Runge_Kutta_Fehlberg_7_8.m was added. test_HPOP.m and Ephemeris.m were modified.
4.0.1

test_HPOP, Density_Jacchia70.m, msis86.m, and nrlmsise00.m were modified.
4.0.0

IAU SOFA 2021-05-12 release was used.
3.3.3

Accel.m, AccelHarmonic_AnelasticEarth.m, AccelHarmonic_ElasticEarth.m, ECEF2ECI.m, ECI2ECEF.m, and nrlmsise00.m were modified to decrease CPU time.
3.3.2

Conical shadow model was added.
3.3.1

It was revised on 2022-10-12.
3.3.0

JB2006.m is added.
3.2.2

The AccelHarmonic_AnelasticEarth.m and the AccelHarmonic_ElasticEarth.m are modified.
3.2.1.1

AccelHarmonic_ElasticEarth.m and Accel.m are modified.
3.1.1.1

The AccelHarmonic_AnelasticEarth.m, the AccelHarmonic_ElasticEarth.m, and the Accel.m are modified.
3.1.1.0

The AccelHarmonic_AnelasticEarth.m and the AccelHarmonic_ElasticEarth.m are modified.
3.1.0.0

The AccelHarmonic_AnelasticEarth.m, the AccelHarmonic_ElasticEarth.m, and the Accel.m are modified.
3.0.0.0

Accel.m and JB2008.m are modified.
2.2.2.2

Mjday_TDB, test_HPOP, and nrlmsise00 are modified.
2.2.2.1

The DE436 full matrix is added.
2.2.1.1

JB2008 is modified.
2.1.1.1

AccelHarmonic_ElasticEarth.m, AccelHarmonic_AnelasticEarth.m, and HPOP.m are modified.
2.1.1.0

AccelHarmonic_ElasticEarth.m and AccelHarmonic_AnelasticEarth.m are modified.
2.1.0.0

HPOP.m, JPL_Eph_DE436.m and SAT_Const.m are modified.
2.0.0.0

Ephemeris.m is modified to decrease CPU time.
DE430 (planetary and lunar ephemerides) is replaced by DE436.
Satellite's ground track is plotted.
Effect of Solid Earth Tides is computed for elastic and anelastic Earth based on IERS Conventions 2010 (AccelHarmonic_ElasticEarth.m, AccelHarmonic_AnelasticEarth.m).
Revised on 2017-12-22.
IERS.m, JB2008.m, nrlmsise00.m, msis86.m, Density_Jacchia70.m, and HPOP.m are modified to decrease CPU time.
SAT_Const.m and constants.m are called once to decrease CPU time.
1.1.0.0

Revised on 2016-11-30.
.
Description is updated.
Integrator, shadow model and atmospheric density model are changed.
The image is added.
1.0.0.0