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Orbit Trajectory Propagation

version 1.0.0 (1.42 MB) by Richard DeMark
Propagation of perturbed and unperturbed orbital trajectories from initial states


Updated 14 Nov 2018

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This LiveScript is designed to propagate any conic section orbit trajectory about a user-selected spherical celestial object within the solar system using Keplerian orbital mechanics. Using only initial postion and velocity state vectors, one can propagate circular, elliptical, parabolic, or hyperbolic orbits about an orbit body over time using a Cowell Method numerical integrator. The example compares the unperturbed two-body propagation with a purturbed propagated orbit due to orbit body spherical oblateness of the same initial state vectors. Once the orbit state vectors are obtained, it plots the orbit trajectories in three dimensions specific to the selected orbit body and see the differences in trajectories.

Cite As

Richard DeMark (2020). Orbit Trajectory Propagation (, MATLAB Central File Exchange. Retrieved .

Comments and Ratings (3)

Yenca Migoya Orue

Sergio Franco Barata

Hongyang Zhou

Nice work! Just mentioning one tiny plotting issue: at least in R2018b, the legend function does not allow text to be the same as keyword argument, so legend('Position') won't work. Instead, we can use legend({'Position'}) to avoid the conflict.

MATLAB Release Compatibility
Created with R2018a
Compatible with any release
Platform Compatibility
Windows macOS Linux
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