MATLAB Functions for Two Body Orbit Propagation
版本 1.0.0.0 (257.6 KB) 作者:
David Eagle
Three MATLAB functions for propagating two-body orbits
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.
引用格式
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. 检索来源 .
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