Code covered by the BSD License  

Highlights from
A MATLAB Script for Computing Hyperbolic Coordinates

4.0 | 2 ratings Rate this file 13 Downloads (last 30 days) File Size: 243 KB File ID: #38886 Version: 1.1

A MATLAB Script for Computing Hyperbolic Coordinates


David Eagle (view profile)


02 Nov 2012 (Updated )

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

| Watch this File

File Information

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.

MATLAB release MATLAB 8.0 (R2012b)
Tags for This File   Please login to tag files.
Please login to add a comment or rating.
Comments and Ratings (2)
23 Oct 2015 Katie Smit

Does anybody know why the true anomaly calculation here on pg. 5 of the .pdf explaination is calculated as theta_inf = acos(-1/e) instead of theta_inf = acos(1/e)?
All the information I've found about calculating true anomaly during a hyperbolic orbit has a positive 1/e within acos.

10 Jun 2014 sun Chong  
29 Jan 2014 1.1

Updated user's manual. Added interactive features to the MATLAB script.

Contact us