### A lot of information is available at the MathWorks
website.

###

### And here’s my bit of stuff that may help.

### A Matlab m-file is a file with extension ".m" that Matlab can
execute. There are two types of m-files: script files and function files.

This file contains basic exercises
to help you become familiar with Matlab's features.

### Rotation matrices

The file rotex.m is a *script*
file that computes some example rotation matrices. It uses the *function*
files R1.m, R2.m, and R3.m. These three
files compute the simple rotation matrices associated with "1",
"2", and "3" rotations, respectively.

You should download these 4 files, put them in your
Matlab directory, and type rotex at the Matlab prompt to see how it works.

### Position and velocity <-> Orbital elements

The file rv2oeex.m is a
script file that does the calculations for a specific problem of converting
position and velocity vectors to orbital elements. It calls two Matlab
functions rv2oe.m
and oe2rv.m
to convert between position and velocity and orbital elements. In these
functions, oe is a 6x1 matrix containing the semimajor axis, eccentricity,
inclination, argument of periapsis, right ascension of the ascending node, and
true anomaly (at epoch). A variation on oe2rv.m is oee2rv.m. The
difference is that the 6th orbital element in the oee2rv version is eccentric
anomaly at epoch instead of true anomaly.

### SEZ coordinates -> Position and velocity

The file razel2rv.m is
a Matlab function that converts rho, rhodot, Az, Azdot, El, and Eldot to
position and velocity vectors in the IJK frame. You do need to know local
sidereal time, Earth rotation rate (relative to inertial space), site latitude,
and Earth radius.

The file razelex.m is a
Matlab script file that does an example, including making a plot of the
three-dimensional trajectory intersecting a sphere.

- Read a Two-Line Element Set
and put the classical orbital elements into a 6x1 matrix: tle2oee.m.
Note that the 6th orbital element is eccentric anomaly at epoch. A version
with true anomaly at epoch as the 6th element is available in the zip file
below.
- Download a collection of
useful astrodynamics functions. They're zipped up in astro.zip.
- Read my “manifesto”
on numerical integration using Matlab.