| Re: Satellite orbit procedure [message #29582] |
Wed, 06 March 2002 06:50  |
Craig Markwardt
Messages: 1869
Registered: November 1996
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Senior Member |
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Richard Lord <Richard.Lord@dlr.de> writes:
> Hi,
>
> I'm looking for a procedure that takes as input the parameters of a
> satellite orbit (Kepler orbit parameters), and outputs so-called
> statevectors. A statevector contains the x,y,z and vx,vy,vz
> coordinates at any particular point in time.
>
> If anybody has seen a procedure that does something along the lines
> explained above, I would be grateful to receive a copy.
Hi Richard--
This kind of code can also be found in the HELIO procedure in the IDL
Astronomy Library. You have to be aware that this kind of code is
only really good for bodies in the solar system. For near earth
objects the story is a little different. The so-called "mean" orbital
elements are also tied to an orbital model, like the SGP4. You would
need to propagate the orbit using this model.
Good luck,
Craig
--
------------------------------------------------------------ --------------
Craig B. Markwardt, Ph.D. EMAIL: craigmnet@cow.physics.wisc.edu
Astrophysics, IDL, Finance, Derivatives | Remove "net" for better response
------------------------------------------------------------ --------------
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| Re: Satellite orbit procedure [message #29583 is a reply to message #29582] |
Wed, 06 March 2002 06:58  |
Liam E. Gumley
Messages: 378
Registered: January 2000
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Senior Member |
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Richard Lord wrote:
> I'm looking for a procedure that takes as input the parameters of a
> satellite orbit (Kepler orbit parameters), and outputs so-called
> statevectors. A statevector contains the x,y,z and vx,vy,vz
> coordinates at any particular point in time.
I looked into this problem a while ago. The most convenient solution I
found was the "Satellite Tool Kit" (STK) software freely available from
http://www.stk.com/
The free version of their software accepts Keplerian elements (e.g.
NORAD TLE format) and computes the corresponding state vectors
propagated forward in time.
The STK software is unrelated to IDL.
Cheers,
Liam.
Practical IDL Programming
http://www.gumley.com/
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| Re: Satellite orbit procedure [message #29655 is a reply to message #29582] |
Thu, 28 February 2002 08:32 |
Ed Wright
Messages: 39
Registered: February 1999
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Member |
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in article 3C7E3189.88B08ED3@dlr.de, Richard Lord at Richard.Lord@dlr.de
wrote on 2/28/02 5:32 AM:
>
> Hi,
>
> I'm looking for a procedure that takes as input the parameters of a
> satellite orbit (Kepler orbit parameters), and outputs so-called
> statevectors. A statevector contains the x,y,z and vx,vy,vz
> coordinates at any particular point in time.
>
> If anybody has seen a procedure that does something along the lines
> explained above, I would be grateful to receive a copy.
>
> Thanks in advance,
> Richard
Give me another month and I'll finish testing a dlm interface to the JPL
CSPICE library. The library includes routines for orbit computations, time
conversion, and associated functions.
As always,
Ed Wright
JPL/NAIF
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