A MATLAB implementation of R. H. Gooding's method for converting an ECI state vector to classical orbital elements. Valid for elliptical and hyperbolic orbits. Reference: R. H. Gooding, "On Universal Elements, and Conversion Procedures To and From Position and Velocity", Celestial Mechanics 44 (1988), 283-298
David Eagle (2020). Gooding's State Vector-to-Orbital Elements Algorithm (https://www.mathworks.com/matlabcentral/fileexchange/48590-gooding-s-state-vector-to-orbital-elements-algorithm), MATLAB Central File Exchange. Retrieved .