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 and applied astrodynamics. MATLAB Scripts and functions are provided for
solving spaceflight 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 MATLAB 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 Orbital Mechanics with MATLAB can be downloaded here.
Last updated
January 5, 2012
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
Aerospace
Trajectory Optimization Using Direct Transciption
(SNOPT)
PLEASE NOTE: The MATLAB scripts flagged with (SNOPT) were
written for use with the SNOPT nonlinear programming (NLP) algorithm. MATLAB versions of SNOPT 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. These
scripts have been tested with Windows XP Professional (32 bit), Windows 7 Home Premium
(32 bit), versions R2010a and R2010b of MATLAB, and the 12/30/2010 version of
SNOPT.
DOWNLOADS
Bi-elliptic Transfer Between Coplanar Circular Orbits Zipped file of MATLAB
source code and PDF user's guide
Transfer Angle Between Two
Position Vectors Zipped
file of MATLAB source code and PDF user's guide
Optimal Single Impulse
De-orbit from Earth Orbits Zipped
file of MATLAB source code and PDF user's guide (SNOPT)
Demo Script for Hyperbolic
Coordinates Zipped
file of MATLAB source code
Demo Script for the NOVAS
3.0 Sidereal Time Zipped
file of MATLAB source code
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
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)
Web site contents copyright © 1996-2012 by C. David
Eagle.
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cdeaglejr@yahoo.com www.cdeagle.com