| getMu() |  | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| createTLE() |  | 100% | | n/a | 0 | 1 | 0 | 9 | 0 | 1 |
| of(TLE, Frame) | | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
| SGP4OrbitalState(AbsoluteDate, AveragedKeplerianWithMeanAngle, Frame, TimeScale) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
| SGP4OrbitalState(AbsoluteDate, AveragedKeplerianWithMeanAngle, DataContext) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| computeMeanMotion(double) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| computeSemiMajorAxis(TLE) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| createPropagator() | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| toOsculatingOrbit() | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| SGP4OrbitalState(AbsoluteDate, AveragedKeplerianWithMeanAngle) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getAveragedElements() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getTleMu() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getOrbitType() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getPositionAngleType() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |