Orbital Mechanics Library

A compilation of all of the functions I wrote for my orbital mechanics class

Description

There are 23 different functions performing basic orbital operations (Hohmann tx, inclination and node changes, orbital parameter conversions, ground tracks, orbit plotting, etc.). Some of these functions are still rough, so please provide feedback. These functions are basically how I did all of my homework. There are a few plotting functions that are "just for fun" i.e. I'm being a geek. Please e-mail me if you have problems, suggestions, comments, or snide remarks.

• MATLAB release: MATLAB 6.5 (R13)

[Jared Teneyck]

Written Poorly and slow to run. Many better programs out there.

[Chris Simpson]

Code needs some improvements on speed. Many functions(zeroTo360 prime example) are way overwritten

[Brent Lewis]

Useful program for aerospace

[heidi skhiri]

the best...

[John Parsi]

very useful !
the codes are clear and understandable

[Christopher Defoor]

Better Comments of where things came from would be helpful

[Jo Man]

I think KeplerCOE.m has a bug in it because when I run:

[ newPos, newVel ] = KeplerCOE( pos, vel, 0 );
norm( newPos - pos ) is a lot bigger than zero.

[sandip aghav]

good help

[Gerhard Hejc]

There is a bug in the function "eci2ecef". The transformation of the velocity vector from ECI to ECEF frame is not correct. The line V_ECEF(:,j) = R3(GST(j))*V_ECI(:,j) has to be replaced by something like

EARTH_RATE = 7.2921151467e-5;
V_R = cross([ 0 0 EARTH_RATE ], ECI(:,j));
V_ECEF(:,j) = R3(GST(j))*(V_ECI(:,j) - V_R');