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Astro::Coord::ECI::TLE - Compute satellite locations using NORAD orbit propagation models |
Astro::Coord::ECI::TLE - Compute satellite locations using NORAD orbit propagation models
my @sats = Astro::Coord::ECI::TLE->parse ($tle_data);
my $now = time ();
foreach my $tle (@sats) {
my @latlon = $tle->universal ($now)->geodetic ();
my @xyz = $tle->eci (); # For same time.
print $tle->get ('id'), "\t@latlon\t@xyx\n";
}
The acquisition of the orbital elements represented by $tle_data in the above example is left as an exercise for the student.
Hint: see http://www.space-track.org/, http://celestrak.com/, or the Astro::SpaceTrack manpage.
This module implements the NORAD orbital propagation models described in their ``SPACETRACK REPORT NO. 3, Models for Propagation of NORAD Element Sets.'' In other words, it turns the two- or three-line element sets available from such places as http://www.space-track.org/ or http://celestrak.com/ into predictions of where the relevant orbiting bodies will be. This module does not implement a complete satellite prediction system, just the NORAD models.
The models implemented are:
SGP - fairly simple, only useful for near-earth bodies; SGP4 - more complex, only useful for near-earth bodies; SDP4 - corresponds to SGP4, but for deep-space bodies; SGP8 - more complex still, only for near-earth bodies; SDP8 - corresponds to SGP8, but for deep-space bodies.
There are also some meta-models, with the smarts to run either a near-earth model or the corresponding deep-space model depending on the body the object represents:
model - uses the preferred model (sgp4 or sdp4); model4 - runs sgp4 or sdp4; model8 = runs sgp8 or sdp8.
The models do not return the coordinates directly, they simply set the coordinates represented by the object (by virtue of being a subclass of Astro::Coord::ECI) and return the object itself. You can then call the appropriate inherited method to get the coordinates of the body in whatever coordinate system is convenient.
It is also possible to run the desired model (as specified by the model attribute) simply by setting the time represented by the object.
At the moment, the recommended model to use is either SGP4 or SDP4, depending on whether the orbital elements are for a near-earth or deep-space body. For the purpose of these models, any body with a period of at least 225 minutes is considered to be a deep-space body.
The NORAD report claims accuracy of 5 or 6 places a day after the epoch of an element set for the original FORTRAN IV, which used (mostly) 8 place single-precision calculations. Perl typically uses many more places, but it does not follow that the models are correspondingly more accurate when implemented in Perl.
This class is a subclass of Astro::Coord::ECI. This means that the models do not return results directly. Instead, you call the relevant Astro::Coord::ECI method to get the coordinates you want. For example, to find the latitude, longitude, and altitude of a body at a given time, you do
my ($lat, $long, $alt) = $body->model ($time)->geodetic;
Or, assuming the model attribute is set the way you want it, by
my ($lat, $long, $alt) = $body->geodetic ($time);
This module is a computer-assisted translation of the FORTRAN reference implementation in ``SPACETRACK REPORT NO. 3.'' That means, basically, that I ran the FORTRAN through a Perl script that handled the translation of the assignment statements into Perl, and then fixed up the logic by hand. Dominik Borkowski's SGP C-lib was used as a reference implementation for testing purposes, because I didn't have a Pascal compiler, and I have yet to get any model but SGP to run correctly under g77.
The following methods should be considered public:
new()Any arguments get passed to the set() method.
It is both anticipated and recommended that you use the parse()
method instead of this method to create an object, since the models
currently have no code to guard against incomplete data.
ds50($time)It can also be called as a ``static'' method, i.e. as Astro::Coord::ECI::TLE->ds50 ($time), but in this case the time may not be defaulted, and no attempt has been made to make this a pretty error.
get('attribute')model($time)The intent is that this method will use whatever model is currently preferred. If the preferred model changes, this method will use the new preferred model as soon as I:
- Find out about the change; - Can get the specifications for the new model; - Can find the time to code up the new model.
You need to call one of the Astro::Coord::ECI methods (e.g. geodetic () or equatorial ()) to retrieve the position you just calculated.
You need to call one of the Astro::Coord::ECI methods (e.g. geodetic () or equatorial ()) to retrieve the position you just calculated.
You need to call one of the Astro::Coord::ECI methods (e.g. geodetic () or equatorial ()) to retrieve the position you just calculated.
The input will be split into individual lines, and all blank lines and lines beginning with '#' will be eliminated. The remaining lines are assumed to represent two- or three-line element sets, in so-called external format. Internal format (denoted by a 'G' in column 79 of line 1 of the set, not counting the common name if any) is not supported, and the presence of such data will result in an exception being thrown.
Because this is a subclass of Astro::Coord::ECI, any attributes of that class can also be set.
sgp($time)The result is the original object reference. You need to call one of the Astro::Coord::ECI methods (e.g. geodetic () or equatorial ()) to retrieve the position you just calculated.
``Spacetrack Report Number 3'' (see ``Acknowledgments'') says that this model can be used for either near-earth or deep-space orbits, but the reference implementation they provide dies on an attempt to use this model for a deep-space object, and I have followed the reference implementation.
sgp4($time)The result is the original object reference. See the DESCRIPTION heading above for how to retrieve the coordinates you just calculated.
``Spacetrack Report Number 3'' (see ``Acknowledgments'') says that this model can be used only for near-earth orbits.
sdp4($time)The result is the original object reference. You need to call one of the Astro::Coord::ECI methods (e.g. geodetic () or equatorial ()) to retrieve the position you just calculated.
``Spacetrack Report Number 3'' (see ``Acknowledgments'') says that this model can be used only for deep-space orbits.
sgp8($time)The result is the original object reference. You need to call one of the Astro::Coord::ECI methods (e.g. geodetic () or equatorial ()) to retrieve the position you just calculated.
``Spacetrack Report Number 3'' (see ``Acknowledgments'') says that this model can be used only for near-earth orbits.
sdp8($time)The result is the original object reference. You need to call one of the Astro::Coord::ECI methods (e.g. geodetic () or equatorial ()) to retrieve the position you just calculated.
``Spacetrack Report Number 3'' (see ``Acknowledgments'') says that this model can be used only for near-earth orbits.
Although there is no reason this method can not be called directly, it exists to take advantage of the hook in the Astro::Coord::ECI object, to allow the position of the body to be computed when the time of the object is set.
This class has the following public attributes. The description gives the data type. It may also give one of the following if applicable:
parse - if the attribute is set by the parse() method;
read-only - if the attribute is read-only;
static - if the attribute may be set on the class.
Note that the orbital elements provided by NORAD are tweaked for use by the models implemented by this class. If you plug them in to the same-named parameters of other models, your mileage may vary significantly.
payload(s) getting the
first letters, and spent boosters, debris, etc getting the rest.
time_set() method is called, or a
false value if no model is to be run. Legal model names are: model,
model4, model8, sgp, sgp4, sgp8, sdp4, and sdp8.
The default is 'model'. Setting the value on the class changes the default.
parse() method to
generate this object.
The author wishes to acknowledge the following individuals.
Dominik Brodowski (http://www.brodo.de/), whose SGP C-lib (available at http://www.brodo.de/space/sgp/) provided a reference implementation that I could easily run, and pick apart to help get my own code working. Dominik based his work on Dr. Kelso's Pascal implementation.
Felix R. Hoots and Ronald L. Roehric, the authors of ``SPACETRACK REPORT NO. 3 - Models for Propagation of NORAD Element Sets,'' which provided the basis for the Astro::Coord::ECI::TLE module.
Dr. T. S. Kelso, who compiled this report and made it available at http://celestrak.com/NORAD/documentation/spacetrk.pdf. Dr. Kelso's Two-Line Element Set Format FAQ (http://celestrak.com/columns/v04n03/) was also extremely helpful, as was his discussion of the coordinate system used (http://celestrak.com/columns/v02n01/) and (indirectly) his Pascal implementation of these models.
I am aware of no other modules that perform calculations with NORAD orbital element sets. The Astro-Coords package by Tim Jenness provides calculations using orbital elements, but the NORAD elements are tweaked for use by the models implemented in this package.
Thomas R. Wyant, III (wyant at cpan dot org)
Copyright 2005, 2006 by Thomas R. Wyant, III (wyant at cpan dot org). All rights reserved.
This module is free software; you can use it, redistribute it and/or modify it under the same terms as Perl itself. Please see http://perldoc.perl.org/index-licence.html for the current licenses.
This software is provided without any warranty of any kind, express or implied. The author will not be liable for any damages of any sort relating in any way to this software.
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Astro::Coord::ECI::TLE - Compute satellite locations using NORAD orbit propagation models |