Documentation for C++ NORAD SGP4/SDP4 Implementation
Developed by Michael F. Henry
December, 2003
Copyright © 2003-2009. All rights reserved.
Permission to use for non-commercial purposes only.
All other uses contact author at mfh@zeptomoby.com
The files in this package implement the SGP4 and SDP4 algorithms described in the
December, 1980 NORAD document "Space Track Report No. 3". The report provides
FORTRAN IV implementations of each. These two orbital models, one for "near-earth"
objects and one for "deep space" objects, are widely used in satellite tracking software
and can produce very accurate results when used with current NORAD two-line element
datum.
The original NORAD FORTRAN IV SGP4/SDP4 implementations were converted to
Pascal by Dr. TS Kelso in 1995. This work formed the basis of a modern, object-
oriented C++ implementation by the author in 2002.
The project files were compiled using Microsoft Visual Studio 7.0.
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A brief description of important classes:
cTle This class encapsulates a single set of NORAD two line elements.
cEci This class encapsulates Earth-Centered Inertial coordinates and velocity for a
given moment in time.
cOrbit Given a cTle object, this class provides information about the orbit of the
described satellite, including inclination, perigee, eccentricity, etc. Most importantly, it
provides ECI coordinates/velocity for the satellite.
CSite Describes a location on the earth. Given the ECI coordinates of a satellite, this
class can generate Azimuth/Elevation look angles to the satellite.
cNoradBase, cNoradSGP4, cNoradSDP4 These classes implement the NORAD
SGP4/SDP4 algorithms. They are used by cOrbit to calculate the ECI
coordinates/velocity of its associated satellite.
For excellent information on the underlying physics of orbits, visible satellite
observations, current NORAD TLE data, and other related material, see
http://www.celestrak.com which is maintained by Dr. TS Kelso.
Michael F. Henry
December, 2003
(Updated January, 2009)
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