A MATLAB Script for Computing Hyperbolic Coordinates

PDF user’s manual and source code for a MATLAB script named demo_hyper that can be used to calculate C3 (twice the specific (per unit mass) orbital energy), RLA (the right ascension) and DLA (declination) of the asymptote of a hyperbolic trajectory. The script can use both Cartesian state vector (position and velocity vectors) and classical orbital elements as the data source.

This computer program assumes that the hyperbolic targets, state vector and classical orbital elements are all in the same Earth-centered-inertial (ECI) coordinate system.