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. Several stand-alone applications and major
components of the Orbital Mechanics with MATLAB software
suite are also available for purchase.
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.
The MATLAB source code for the stand-alone application, Numerical Prediction of Orbital Events
(NPOE) is available for $79. (This
application is included in the complete collection).
Click
here to order the NPOE application ($79).
The password protected zipped file for NPOE can be downloaded here. The PDF documentation for NPOE can
be downloaded here.
The MATLAB source code for the astrodynamic
coordinates routines is available
for $79. (These routines are included in
the complete collection).
Click
here to order the coordinates routines ($79). The password protected zipped file for these
routines can be downloaded here. The PDF documentation for these
routines can be downloaded here.
The MATLAB source code for the ephemeris
routines is available for $79. (These
routines are included in the complete collection).
Click
here to order the ephemeris routines ($79).
The password protected zipped file for these routines can be downloaded here. The PDF documentation for these
routines can be downloaded here.
The MATLAB source code for the numerical
methods and utility routines is available for $59. (These routines are included in the complete
collection).
Click
here to order the numerical methods and utility routines ($59). The password protected zipped file for these
routines can be downloaded here. The PDF documentation for these routines
can be downloaded here.
The MATLAB source code for the programmer’s
toolbox is available for $99. (These
routines are included in the complete collection).
Click
here to order the programmer's toolbox routines ($99). The password protected zipped file for these
routines can be downloaded here. The PDF documentation for these
routines can be downloaded here.
Last updated July 2, 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
Shadow1 Zipped file
of MATLAB pcode
Hohmann Orbit Transfer Zipped file
of MATLAB pcode
Geosync1 Zipped file
of MATLAB pcode
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
This
script illustrates a typical use 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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site contents copyright © 1996-2009 by C. David Eagle. All rights reserved.
cdeaglejr@yahoo.com www.cdeagle.com