MATLAB Functions for Two Body Orbit Propagation

Three MATLAB functions for propagating two-body orbits
Updated 11 Dec 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.

Cite As

David Eagle (2024). MATLAB Functions for Two Body Orbit Propagation (, MATLAB Central File Exchange. Retrieved .

MATLAB Release Compatibility
Created with R2014b
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