A MATLAB Script for Computing Hyperbolic Coordinates

This script demonstrates how to compute C3, RLA, and DLA of a hyperbolic orbit.

This submission is a MATLAB script named demo_hyper that can be used to calculate C3 (twice the specific (per unit mass) orbital energy), RLA (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.