MATLAB Functions for Two Body Orbit Propagation

Version 1.0.0.0 (258 ko) par David Eagle
Three MATLAB functions for propagating two-body orbits
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Mise à jour 11 déc. 2014

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PDF document and three MATLAB functions that can be used to propagate two body or “unperturbed” satellite orbits. This type of propagation is also called the orbital initial value problem (IVP). All three algorithms are valid for elliptical and hyperbolic orbits, and each numerical method can propagate forward or backward in time. For programming flexibility, the input and output arguments for each routine are identical.

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David Eagle (2024). MATLAB Functions for Two Body Orbit Propagation (https://www.mathworks.com/matlabcentral/fileexchange/48723-matlab-functions-for-two-body-orbit-propagation), MATLAB Central File Exchange. Récupéré le .

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Créé avec R2014b
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Version Publié le Notes de version
1.0.0.0