文件列表:

SxP4Test\cEci.cpp (3642, 2005-10-16)
SxP4Test\cEci.h (1344, 2005-09-29)
SxP4Test\cJulian.cpp (7381, 2005-10-06)
SxP4Test\cJulian.h (2467, 2005-10-06)
SxP4Test\cNoradBase.cpp (9469, 2005-10-06)
SxP4Test\cNoradBase.h (1647, 2005-09-29)
SxP4Test\cNoradSDP4.cpp (24817, 2005-10-06)
SxP4Test\cNoradSDP4.h (3238, 2005-09-29)
SxP4Test\cNoradSGP4.cpp (4035, 2005-10-06)
SxP4Test\cNoradSGP4.h (690, 2005-09-29)
SxP4Test\coord.cpp (672, 2005-09-29)
SxP4Test\coord.h (1131, 2005-09-29)
SxP4Test\cOrbit.cpp (4506, 2005-10-06)
SxP4Test\cOrbit.h (3207, 2005-10-15)
SxP4Test\cSite.cpp (7344, 2008-10-29)
SxP4Test\cSite.h (1102, 2008-10-29)
SxP4Test\cTLE.cpp (12359, 2005-09-29)
SxP4Test\cTLE.h (5241, 2005-09-29)
SxP4Test\cVector.cpp (1767, 2005-09-29)
SxP4Test\cVector.h (761, 2005-09-29)
SxP4Test\Debug\cEci.obj (37589, 2008-10-29)
SxP4Test\Debug\cEci.sbr (0, 2008-10-29)
SxP4Test\Debug\cJulian.obj (34372, 2008-10-29)
SxP4Test\Debug\cJulian.sbr (0, 2008-10-29)
SxP4Test\Debug\cNoradBase.obj (129882, 2008-10-29)
SxP4Test\Debug\cNoradBase.sbr (0, 2008-10-29)
SxP4Test\Debug\cNoradSDP4.obj (81225, 2008-10-29)
SxP4Test\Debug\cNoradSDP4.sbr (0, 2008-10-29)
SxP4Test\Debug\cNoradSGP4.obj (32367, 2008-10-29)
SxP4Test\Debug\cNoradSGP4.sbr (0, 2008-10-29)
SxP4Test\Debug\coord.obj (22682, 2008-10-29)
SxP4Test\Debug\coord.sbr (0, 2008-10-29)
SxP4Test\Debug\cOrbit.obj (78922, 2008-10-29)
SxP4Test\Debug\cOrbit.sbr (0, 2008-10-29)
SxP4Test\Debug\cSite.obj (82510, 2008-10-29)
SxP4Test\Debug\cSite.sbr (0, 2008-10-29)
SxP4Test\Debug\cTLE.obj (177190, 2008-10-29)
SxP4Test\Debug\cTLE.sbr (0, 2008-10-29)
SxP4Test\Debug\cVector.obj (10957, 2008-10-29)
SxP4Test\Debug\cVector.sbr (0, 2008-10-29)
... ...

Documentation for C++ NORAD SGP4/SDP4 Implementation Developed by Michael F. Henry December, 2003 Copyright 2003-2006. All rights reserved. The files in this package implement the SGP4 and SDP4 algorithms described in the December, 1***0 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. In 1996 these routines were ported in a straight-forward manner to C++ by Varol Okan. The SGP4/SDP4 classes here were written by Michael F. Henry in 2002-03 and are a modern C++ re-write of the work done by Okan. In addition to introducing an object-oriented architecture, the last residues of the original FORTRAN code (such as labels and gotos) were eradicated. The project files were compiled using Microsoft Visual Studio 7.0. Any compiler that supports the C++ Standard Template Library should work, including Visual Studio 6.0. The project generates a single executable, SxP4Test.exe, which calculates ECI position and velocity information for the test element sets originally published in the NORAD report. Also provided as an additional example is how to use the classes to calculate the look angle from a location on the earth to a satellite in orbit. Here is the correct program output: SGP4 Test 1 88888U 80275.***708465 .00073094 13844-3 66816-4 0 8 2 88888 72.8435 115.9689 0086731 52.6***8 110.5714 16.05824518 105 TSINCE X Y Z 0.00 2328.97070437 -5995.22083333 1719.97065611 360.00 2456.10787343 -6071.93868176 1222.89554078 720.00 2567.56296224 -6112.50380175 713.96182588 1080.00 2663.09017513 -6115.48274470 196.39907463 1440.00 2742.55440194 -6079.66***4186 -326.39149750 XDOT YDOT ZDOT 2.91207225 -0.***341531 -7.09081697 2.67938906 -0.44828838 -7.22879265 2.44024485 0.0***11117 -7.31995951 2.19612076 0.65241695 -7.36282421 1.94849696 1.21107421 -7.35619305 SDP4 Test 1 11801U 80230.29629788 .01431103 00000-0 14311-1 8 2 11801 46.7916 230.4354 7318036 47.4722 10.4117 2.28537848 6 TSINCE X Y Z 0.00 7473.37213351 428.95462549 5828.74786677 360.00 -3305.22417***5 32410.86360001 -24697.17732308 720.00 14271.28695394 24110.46300337 -4725.76750899 1080.00 -9990.05752318 22717.36123***3 -23616.89356***1 1440.00 9787.87233694 33753.34427732 -15030.80628319 XDOT YDOT ZDOT 5.10715289 ***4468289 -0.18613182 -1.30113547 -1.15131513 -0.28333528 -0.32050442 2.67***4097 -2.08405301 -1.01667268 -2.29026701 0.72892308 -1.09425038 0.92358954 -1.52230979 Example output: AZ: 100.2 EL: 12.8 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

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