Statements (32)
| Predicate | Object |
|---|---|
| gptkbp:instanceOf |
satellite orbit propagation model
|
| gptkbp:category |
gptkb:astrodynamics
space situational awareness |
| gptkbp:developedBy |
gptkb:United_States_Air_Force
|
| gptkbp:documentation |
Spacetrack Report No. 3
|
| gptkbp:format |
two-line element set (TLE)
|
| gptkbp:fullName |
Simplified General Perturbations 4
|
| gptkbp:hasModel |
atmospheric drag
Earth's oblateness Earth's gravitational perturbations |
| https://www.w3.org/2000/01/rdf-schema#label |
SGP4 model
|
| gptkbp:introducedIn |
1960s
|
| gptkbp:limitation |
accuracy decreases over time
not suitable for deep space objects not suitable for high-altitude orbits |
| gptkbp:openSource |
Orekit
libsgp4 pyorbital python-sgp4 |
| gptkbp:output |
satellite position and velocity
|
| gptkbp:relatedTo |
SDP4 model
SDP8 model SGP8 model |
| gptkbp:replacedBy |
SGP model
|
| gptkbp:supportsAlgorithm |
analytical orbit propagator
|
| gptkbp:usedBy |
gptkb:Celestrak
NORAD satellite tracking software |
| gptkbp:usedFor |
predicting satellite positions
propagating two-line element sets (TLEs) |
| gptkbp:bfsParent |
gptkb:Two-Line_Element_Set_(TLE)
|
| gptkbp:bfsLayer |
7
|