Code covered by the BSD License
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sat_orbit
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[n,u]=my_const(c)
CONSTANT Get physical constant.
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ecef2enu(V_ecef, O_ecef)
ECEF2ENU conversion
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eci2ecef(TIME, R_ECI, V_ECI)%...
October 1, 2006
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enu2ecef(V_enu, O_ecef)
ENU2ECEF conversion
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invjday ( jd );
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jday(yr, mon, day, hr, min, s...
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llh2xyz(lat,long, h)
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norad4(tlefile, satname, Nsv2...
ORBIT propagation by NORAD's SGP4
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sat=mytle(tlefile, satname)
TLE2ORB Get Keplerian elements from Two-Line Element data.
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xyz2enu(Xr, Yr, Zr, X, Y, Z)
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xyz2llh(X,Y,Z)
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| File Information |
| Description |
The routine ingest a TLE file and extracts informations from a selceted satellite. Calls orbit propagator SGP4 from http://www.centerforspace.com/downloads/files/sgp4/AIAA-2006-6753Code.zip.
It then converts orbit in the ECI reference into Earth Centered Earth Fixed and also into Lat Long Heigth. The subroutine includes an example of ENVISAT satellite where the accuracy of the propagated orbit is checked with respect over a high precision reference. |
| MATLAB release |
MATLAB 7.7 (R2008b)
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| 12 Oct 2009 |
SU
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