Orbital Mechanics with
MATLAB
Welcome
This web
site describes a comprehensive collection of MATLAB scripts and functions
called Orbital Mechanics with MATLAB. This software can be used to solve a variety
of practical problems in orbital mechanics.
MATLAB Scripts and functions are provided for solving astrodynamic
problems in the areas of orbit design, event prediction and trajectory
optimization. All scripts and support
functions require MATLAB version 7.2 (R2006a) or higher.
The
complete collection of scripts and functions can be purchased for $279. The
software can be ordered using the secure and flexible e-commerce services
provided by PayPal (www.paypal.com). PayPal accepts online payments by
credit card and a PayPal account is not required to make a purchase. Before placing an order, please read the license agreement. After placing your order, you will receive an
email within 24 hours with a password that will permit you to extract the MATLAB
source code and any support data files.
Click
here to order the complete software suite ($279). The password protected zipped file for the
complete collection can be downloaded here.
Last
updated December 11, 2009
Thanks for visiting.
The following is
a list of the analysis scripts and functions included in the complete software
suite. Click on the title to view or
download the PDF documentation.
Orbital Periods of a
Satellite
Rise and Set of Earth
Satellites
Shadow Conditions of Earth
Satellites
Predicting Mutual Visibility
and Close Approach Conditions
Coverage Characteristics of
Earth Satellites
Relative Motion Between Two
Earth Satellites
Circular-Restricted Three-Body
Problem
Graphics Display of
Satellite Ground Tracks, Orbits and Maps
Numerical Methods and
Utility Functions
Numerical Prediction of Orbital
Events
Optimal Impulsive Orbital
Transfer Analysis (SNOPT)
Aerospace Trajectory
Optimization Using Direct Transciption (SNOPT)
PLEASE NOTE: The MATLAB scripts marked with SNOPT were
written for use with the SNOPT nonlinear programming (NLP) algorithm. MATLAB versions of SNOPT 6.0 for several
computer platforms can be found at Professor Philip Gill’s web site which is
located at http://scicomp.ucsd.edu/~peg/. A PDF version of the SNOPT user’s manual is
also available at that website.
DOWNLOADS
Orbital Periods of a Satellite Zipped file of MATLAB source
code
Convert Earth Longitude to Right
Ascension Zipped file of MATLAB
source code
Orbital Elements of a Flyby Hyperbola Zipped file of MATLAB
source code
Bi-elliptic Transfer Between Coplanar
Circular Orbits Zipped file of MATLAB
source code and PDF user's guide
Please note that these binary ephemeris files are
compatible with Windows computers.
SLP96 ephemeris binary data file
(~6 MB)
JPL DE405 ephemeris binary data
file (~6 MB)
JPL DE421 ephemeris binary data
file (~14 MB)
INPOP06c ephemeris binary data
file (~17 MB)
INPOP08a ephemeris binary data
file (~17 MB)
Zipped file of MATLAB source code
These scripts illustrate
several applications of the JPL MICE library.
MICE is a MATLAB implementation of many of the JPL SPICE routines. Additional information about MICE and SPICE
along with downloadable software and documentation can be found at http://naif.jpl.nasa.gov/naif/.
This script is a MICE
version of Cowell’s method for geocentric spacecraft.
Main script (cowell_mice.m)
Equations of motion function (ceqm_mice.m)
Output text file (example.txt)
This script computes the
state vector of the Moon at the DE405 integration epoch.
Main script (de405_integration_epoch.m)
Output text
file (de405_integration_epoch.txt)
This script performs the
EME to/from true-of-date transformation.
Main script (eme_tod_mice.m)
Output text file (eme_tod_mice.txt)
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