Results from TLE & SGP4 propagation - don't seem right & with interpretation

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SUMMARY

The forum discussion centers on issues encountered while using the C++ SGP4 propagator with a TLE of the ISS. The user reported discrepancies in the computed position and velocity vectors, specifically a calculated altitude of approximately 6500 km, which contradicts the known altitude of the ISS at around 100 km. Additionally, the time output indicated an incorrect date of December 61, 1995, leading to confusion. The user concluded that the TLE data sourced online was likely erroneous, highlighting the importance of verifying TLE accuracy when performing satellite propagation.

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thor36
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Greetings all !
I have this problem with SGP4 propagation, that I hope someone can help me out with.

I acquired a TLE of the ISS from internet and used the C++ SGP4 propagator to compute future position and velocity vectors of the Station. I am unsure about some aspects of results though and would like to get some explanations.

The TLE data looks like this :

1 25544U 98067A 14296.89020256 .00021128 00000-0 36676-3 0 2914
2 25544 51.6464 181.6097 0002420 294.7068 172.8232 15.50795889911298​

The settingss I use for the propagator are :

opsmode = i (improved)
typerun = m (manual)
typeinput = m (mfe - minutes from epoch)

I set SGP4 to propagate for 120 minutes after the initial moment in 10 minutes steps. The results are stored in 13 rows ( one for each computation from Tstart to Tend, once every 10 minutes ). It would look really messy to paste the results here, so I will only copy the last line.

R(x) = 4628.43055298
R(y) = 2891.92246591
R(z) = -3530.26416981
V(x) = -5.504313283
V(y) = 3.379764650
V(z) = -4.417716694
Time = 1995 12 61 23:31:53.501202​

So, my questions now :
  1. Position

    I reckoned calculating magnitude of R will result in distance of ISS from the Earth center ( or altitude, if you subtract Earth radius ). But calculating magnitude of this final set of data (posted above) results in a magnitude of approx. 6500 km, which is obviously too small value since we know ISS doesn't orbit the Earth at an altitude of about 100 km. Moreover, if I propagate just two more time steps ( +20 min ) I get error 6 - satellite has decayed. Why such a quick drop in altitude after propagating 140 minutes in future, which is a little more than an orbit and a half for ISS ?
  2. Time

    The last column is supposed to give the time of that particular computation. TLE epoch cell ( 14296.89020256 ) says the year is 2014 at 296th day of the year. But results seem to set the time at 61st December 1995 . Why such result ?
I may be missing something very fundamental, or cannot interpret results properly. I would like to ask for explanations / clarifications that will help me to make use of these ( and all subsequent ) results gained by TLE and SGP4.

Thank you very much and kind regards
T
 
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After doing more "experiments", it seems that the particular TLE I used was erroneous. This was my first testing of SGP4, and many things could be wrong with the code itself, so obviously, the TLE I got from online source wasn't the first thing I blamed for the errors. It seems that even generally reliable online TLE sources can occasionally produce an unfortunate bad instance of a TLE set.
 

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