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From: keithley@apple.com (Craig J. Keithley)
Newsgroups: sci.space,sci.space.shuttle
Subject: Orbital Mechanics formulas
Message-ID: <51540@apple.Apple.COM>
Date: 15 Apr 91 23:07:59 GMT
Sender: keithley@Apple.COM
Organization: Apple Computer Inc, Cupertino, CA
Lines: 26

I'm in need a of a formula that uses:
   The elapsed mission time
   The orbital elements (posted on sci.space[.shuttle])
And returns lat/lon and an altitude

I need to be able to plug in the shuttle (or satellite's) elements
and derive its position above a given spot on the earth.  I'm not
interested in orbital transfer, etc.

I've been told that I should take into account a variety of things,
including orbital decay due to air drag.  How important is it that
these things be taken into account?  If a simple equation provides
99.5% accuracy, I'll probably be happy.  This is because the shuttle's
orbit is probably changing somewhat (due to attitude adjustments),
So I don't expect 100% accuracy anyway.   

While I'd prefer the equation, a book reference would be helpful
also.

Please reply via email, and I'll summarize to the net.

Thanks,

Craig Keithley
Apple Computer, Inc.
keithley@apple.com